NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.85 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9510-il-1000000-n5.txt Download as CSV file: xf-npl9510-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9510 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.1789 0.12410 0.12100 -0.0096 1.0000 0.0126
-19.500 -1.1973 0.11685 0.11365 -0.0133 1.0000 0.0127
-19.250 -1.2156 0.10976 0.10646 -0.0169 1.0000 0.0127
-19.000 -1.2325 0.10302 0.09961 -0.0203 1.0000 0.0128
-18.750 -1.2491 0.09648 0.09296 -0.0235 1.0000 0.0128
-18.500 -1.2633 0.09048 0.08686 -0.0264 1.0000 0.0129
-18.250 -1.2759 0.08481 0.08109 -0.0291 1.0000 0.0129
-18.000 -1.2870 0.07951 0.07568 -0.0316 1.0000 0.0130
-17.750 -1.2962 0.07459 0.07067 -0.0339 1.0000 0.0131
-17.500 -1.3034 0.07008 0.06607 -0.0359 1.0000 0.0132
-17.250 -1.3092 0.06588 0.06177 -0.0378 1.0000 0.0133
-17.000 -1.3131 0.06198 0.05779 -0.0395 1.0000 0.0134
-16.750 -1.3156 0.05838 0.05410 -0.0410 1.0000 0.0135
-16.500 -1.3171 0.05500 0.05064 -0.0423 1.0000 0.0136
-16.250 -1.3175 0.05182 0.04738 -0.0435 1.0000 0.0137
-16.000 -1.3173 0.04884 0.04432 -0.0446 1.0000 0.0138
-15.750 -1.3166 0.04604 0.04144 -0.0455 1.0000 0.0140
-15.500 -1.3148 0.04343 0.03876 -0.0463 1.0000 0.0141
-15.250 -1.3117 0.04098 0.03624 -0.0470 1.0000 0.0142
-15.000 -1.3074 0.03870 0.03388 -0.0476 1.0000 0.0144
-14.750 -1.3018 0.03656 0.03167 -0.0482 1.0000 0.0146
-14.500 -1.2948 0.03459 0.02963 -0.0487 1.0000 0.0147
-14.250 -1.2868 0.03276 0.02773 -0.0491 1.0000 0.0148
-14.000 -1.2781 0.03102 0.02592 -0.0495 1.0000 0.0150
-13.750 -1.2732 0.02895 0.02379 -0.0498 1.0000 0.0152
-13.500 -1.2680 0.02710 0.02189 -0.0498 1.0000 0.0154
-13.250 -1.2650 0.02547 0.02021 -0.0490 1.0000 0.0156
-13.000 -1.2561 0.02399 0.01868 -0.0490 1.0000 0.0159
-12.750 -1.2440 0.02266 0.01731 -0.0492 1.0000 0.0161
-12.500 -1.2289 0.02146 0.01606 -0.0497 1.0000 0.0164
-12.250 -1.2115 0.02042 0.01496 -0.0502 1.0000 0.0167
-12.000 -1.1870 0.01956 0.01404 -0.0515 0.9995 0.0170
-11.750 -1.1585 0.01878 0.01321 -0.0532 0.9985 0.0173
-11.500 -1.1296 0.01807 0.01246 -0.0548 0.9976 0.0177
-11.250 -1.1000 0.01743 0.01176 -0.0564 0.9966 0.0180
-11.000 -1.0702 0.01675 0.01104 -0.0580 0.9957 0.0184
-10.750 -1.0401 0.01611 0.01039 -0.0596 0.9950 0.0190
-10.500 -1.0098 0.01556 0.00981 -0.0611 0.9944 0.0197
-10.250 -0.9797 0.01506 0.00929 -0.0624 0.9937 0.0203
-10.000 -0.9504 0.01461 0.00880 -0.0635 0.9925 0.0210
-9.750 -0.9203 0.01418 0.00834 -0.0646 0.9913 0.0217
-9.500 -0.8897 0.01369 0.00785 -0.0659 0.9902 0.0229
-9.250 -0.8587 0.01328 0.00743 -0.0672 0.9892 0.0243
-9.000 -0.8274 0.01291 0.00704 -0.0685 0.9883 0.0254
-8.750 -0.7959 0.01250 0.00663 -0.0698 0.9875 0.0272
-8.500 -0.7644 0.01213 0.00626 -0.0711 0.9868 0.0291
-8.250 -0.7328 0.01178 0.00591 -0.0724 0.9860 0.0312
-8.000 -0.7012 0.01144 0.00558 -0.0736 0.9853 0.0342
-7.750 -0.6695 0.01110 0.00525 -0.0749 0.9846 0.0377
-7.500 -0.6377 0.01077 0.00494 -0.0761 0.9839 0.0426
-7.250 -0.6079 0.01043 0.00464 -0.0770 0.9823 0.0493
-7.000 -0.5779 0.01007 0.00434 -0.0778 0.9805 0.0590
-6.750 -0.5474 0.00973 0.00406 -0.0788 0.9789 0.0706
-6.500 -0.5165 0.00942 0.00381 -0.0797 0.9773 0.0836
-6.250 -0.4855 0.00913 0.00358 -0.0807 0.9757 0.0960
-6.000 -0.4545 0.00887 0.00337 -0.0816 0.9743 0.1076
-5.750 -0.4233 0.00861 0.00317 -0.0826 0.9730 0.1204
-5.500 -0.3920 0.00836 0.00298 -0.0835 0.9718 0.1352
-5.250 -0.3623 0.00810 0.00280 -0.0841 0.9697 0.1537
-4.750 -0.3025 0.00755 0.00244 -0.0854 0.9649 0.1976
-4.500 -0.2715 0.00704 0.00218 -0.0866 0.9629 0.2557
-4.250 -0.2404 0.00659 0.00196 -0.0877 0.9610 0.3143
-4.000 -0.2097 0.00632 0.00183 -0.0884 0.9593 0.3511
-3.750 -0.1794 0.00614 0.00175 -0.0890 0.9574 0.3792
-3.500 -0.1499 0.00604 0.00170 -0.0894 0.9547 0.3946
-3.250 -0.1204 0.00596 0.00165 -0.0897 0.9520 0.4068
-3.000 -0.0908 0.00589 0.00162 -0.0900 0.9495 0.4172
-2.750 -0.0611 0.00583 0.00159 -0.0903 0.9472 0.4278
-2.500 -0.0314 0.00578 0.00157 -0.0906 0.9451 0.4368
-2.250 -0.0021 0.00573 0.00154 -0.0907 0.9416 0.4442
-2.000 0.0260 0.00566 0.00150 -0.0905 0.9329 0.4562
-1.750 0.0527 0.00558 0.00143 -0.0899 0.9141 0.4684
-1.500 0.0790 0.00559 0.00134 -0.0891 0.8819 0.4767
-1.250 0.1067 0.00564 0.00132 -0.0888 0.8515 0.4846
-1.000 0.1330 0.00584 0.00129 -0.0881 0.7897 0.4898
-0.750 0.1443 0.00832 0.00170 -0.0855 0.2278 0.4937
-0.500 0.1717 0.00868 0.00179 -0.0854 0.1450 0.4977
-0.250 0.1996 0.00893 0.00187 -0.0854 0.0941 0.5017
0.000 0.2279 0.00914 0.00195 -0.0854 0.0640 0.5051
0.250 0.2564 0.00928 0.00203 -0.0855 0.0512 0.5085
0.500 0.2851 0.00940 0.00213 -0.0855 0.0441 0.5122
0.750 0.3137 0.00952 0.00222 -0.0856 0.0400 0.5159
1.000 0.3423 0.00965 0.00233 -0.0856 0.0371 0.5195
1.250 0.3708 0.00978 0.00244 -0.0856 0.0350 0.5226
1.500 0.3993 0.00992 0.00257 -0.0856 0.0331 0.5260
1.750 0.4277 0.01005 0.00271 -0.0855 0.0317 0.5296
2.000 0.4561 0.01019 0.00285 -0.0855 0.0304 0.5331
2.250 0.4844 0.01035 0.00300 -0.0855 0.0293 0.5363
2.500 0.5124 0.01054 0.00318 -0.0854 0.0282 0.5393
2.750 0.5405 0.01071 0.00336 -0.0853 0.0273 0.5426
3.000 0.5687 0.01087 0.00354 -0.0852 0.0265 0.5460
3.250 0.5967 0.01105 0.00373 -0.0851 0.0257 0.5492
3.500 0.6245 0.01124 0.00392 -0.0849 0.0250 0.5524
3.750 0.6522 0.01146 0.00414 -0.0848 0.0243 0.5555
4.000 0.6795 0.01174 0.00442 -0.0845 0.0235 0.5587
4.250 0.7073 0.01192 0.00464 -0.0844 0.0229 0.5622
4.500 0.7350 0.01213 0.00487 -0.0842 0.0223 0.5656
4.750 0.7624 0.01235 0.00512 -0.0840 0.0217 0.5690
5.000 0.7898 0.01259 0.00536 -0.0838 0.0212 0.5722
5.250 0.8170 0.01284 0.00562 -0.0835 0.0206 0.5754
5.500 0.8439 0.01314 0.00594 -0.0832 0.0200 0.5792
5.750 0.8707 0.01345 0.00629 -0.0829 0.0196 0.5830
6.000 0.8976 0.01373 0.00661 -0.0826 0.0193 0.5865
6.250 0.9243 0.01403 0.00694 -0.0822 0.0189 0.5899
6.500 0.9510 0.01432 0.00727 -0.0819 0.0184 0.5933
6.750 0.9777 0.01460 0.00759 -0.0816 0.0179 0.5975
7.000 1.0043 0.01488 0.00789 -0.0812 0.0175 0.6016
7.250 1.0306 0.01519 0.00822 -0.0808 0.0171 0.6055
7.500 1.0562 0.01562 0.00868 -0.0803 0.0167 0.6089
7.750 1.0819 0.01602 0.00914 -0.0798 0.0164 0.6131
8.000 1.1077 0.01641 0.00960 -0.0793 0.0162 0.6177
8.250 1.1331 0.01683 0.01008 -0.0788 0.0159 0.6222
8.500 1.1584 0.01726 0.01057 -0.0783 0.0156 0.6260
8.750 1.1835 0.01769 0.01107 -0.0777 0.0154 0.6303
9.000 1.2084 0.01813 0.01157 -0.0771 0.0151 0.6353
9.250 1.2332 0.01857 0.01208 -0.0765 0.0148 0.6404
9.500 1.2577 0.01904 0.01260 -0.0758 0.0146 0.6450
9.750 1.2819 0.01951 0.01314 -0.0751 0.0144 0.6501
10.000 1.3058 0.02002 0.01371 -0.0744 0.0142 0.6555
10.250 1.3290 0.02062 0.01437 -0.0736 0.0140 0.6610
10.500 1.3510 0.02135 0.01520 -0.0726 0.0137 0.6672
10.750 1.3729 0.02208 0.01603 -0.0716 0.0136 0.6738
11.000 1.3948 0.02276 0.01681 -0.0706 0.0135 0.6798
11.250 1.4160 0.02349 0.01766 -0.0695 0.0134 0.6864
11.500 1.4366 0.02427 0.01856 -0.0683 0.0133 0.6935
11.750 1.4566 0.02507 0.01948 -0.0671 0.0131 0.7005
12.000 1.4761 0.02589 0.02042 -0.0658 0.0130 0.7082
12.250 1.4949 0.02674 0.02138 -0.0644 0.0128 0.7149
12.500 1.5131 0.02759 0.02236 -0.0630 0.0127 0.7221
12.750 1.5302 0.02851 0.02339 -0.0614 0.0125 0.7290
13.000 1.5462 0.02946 0.02447 -0.0597 0.0124 0.7362
13.250 1.5609 0.03049 0.02563 -0.0578 0.0123 0.7444
13.500 1.5742 0.03156 0.02682 -0.0558 0.0122 0.7530
14.000 1.5943 0.03386 0.02941 -0.0509 0.0120 0.7728
14.250 1.5975 0.03506 0.03074 -0.0474 0.0119 0.7843
14.500 1.6003 0.03644 0.03227 -0.0442 0.0118 0.7986
14.750 1.6016 0.03798 0.03398 -0.0410 0.0118 0.8169
15.000 1.6010 0.03972 0.03590 -0.0380 0.0117 0.8432
15.250 1.5951 0.04139 0.03790 -0.0344 0.0117 1.0000
15.500 1.5904 0.04374 0.04038 -0.0319 0.0116 1.0000
15.750 1.5825 0.04655 0.04334 -0.0297 0.0115 1.0000
16.000 1.5704 0.05002 0.04696 -0.0281 0.0115 1.0000
16.250 1.5525 0.05455 0.05167 -0.0275 0.0115 1.0000
16.500 1.5261 0.06090 0.05823 -0.0288 0.0115 1.0000
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