NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-66 (naca001066-il) Reynolds number: 500,000 Max Cl/Cd: 47.13 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001066-il-500000-n5.txt Download as CSV file: xf-naca001066-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0721 0.06953 0.06668 -0.0526 1.0000 0.0078
-15.500 -1.1280 0.05560 0.05244 -0.0612 1.0000 0.0076
-15.250 -1.1577 0.05056 0.04721 -0.0601 1.0000 0.0076
-15.000 -1.1765 0.04654 0.04298 -0.0586 0.9995 0.0076
-14.750 -1.1878 0.04324 0.03948 -0.0568 0.9986 0.0077
-14.500 -1.1948 0.04051 0.03652 -0.0546 0.9975 0.0078
-14.250 -1.1977 0.03817 0.03397 -0.0523 0.9964 0.0079
-14.000 -1.1973 0.03618 0.03177 -0.0498 0.9955 0.0080
-13.750 -1.1975 0.03422 0.02962 -0.0471 0.9947 0.0082
-13.500 -1.1968 0.03261 0.02785 -0.0438 0.9934 0.0084
-13.250 -1.1925 0.03128 0.02638 -0.0408 0.9919 0.0087
-13.000 -1.1848 0.03010 0.02504 -0.0382 0.9905 0.0090
-12.750 -1.1739 0.02902 0.02382 -0.0360 0.9891 0.0093
-12.500 -1.1609 0.02798 0.02263 -0.0342 0.9879 0.0096
-12.250 -1.1466 0.02701 0.02151 -0.0325 0.9870 0.0100
-12.000 -1.1308 0.02609 0.02043 -0.0310 0.9862 0.0105
-11.750 -1.1130 0.02524 0.01942 -0.0298 0.9855 0.0109
-11.500 -1.1073 0.02449 0.01857 -0.0258 0.9830 0.0115
-11.250 -1.0925 0.02387 0.01789 -0.0238 0.9813 0.0122
-11.000 -1.0735 0.02330 0.01723 -0.0226 0.9800 0.0129
-10.750 -1.0526 0.02268 0.01651 -0.0217 0.9789 0.0137
-10.500 -1.0311 0.02204 0.01574 -0.0210 0.9780 0.0146
-10.250 -1.0092 0.02142 0.01504 -0.0203 0.9772 0.0155
-10.000 -0.9851 0.02107 0.01466 -0.0201 0.9765 0.0166
-9.750 -0.9600 0.02076 0.01430 -0.0200 0.9760 0.0178
-9.500 -0.9349 0.02039 0.01383 -0.0199 0.9755 0.0191
-9.250 -0.9231 0.02011 0.01346 -0.0166 0.9730 0.0199
-9.000 -0.9064 0.01964 0.01292 -0.0146 0.9712 0.0208
-8.750 -0.8852 0.01927 0.01253 -0.0136 0.9698 0.0219
-8.500 -0.8614 0.01900 0.01223 -0.0131 0.9686 0.0231
-8.250 -0.8372 0.01872 0.01189 -0.0127 0.9676 0.0244
-8.000 -0.8127 0.01840 0.01148 -0.0123 0.9668 0.0256
-7.750 -0.7874 0.01811 0.01112 -0.0121 0.9662 0.0264
-7.500 -0.7618 0.01782 0.01076 -0.0119 0.9656 0.0271
-7.250 -0.7381 0.01712 0.01002 -0.0115 0.9650 0.0287
-7.000 -0.7124 0.01674 0.00961 -0.0114 0.9646 0.0300
-6.750 -0.6860 0.01642 0.00925 -0.0114 0.9642 0.0311
-6.500 -0.6797 0.01625 0.00904 -0.0067 0.9604 0.0319
-6.250 -0.6594 0.01598 0.00872 -0.0053 0.9586 0.0329
-6.000 -0.6370 0.01570 0.00840 -0.0043 0.9574 0.0339
-5.750 -0.6135 0.01542 0.00807 -0.0035 0.9563 0.0346
-5.500 -0.5891 0.01516 0.00776 -0.0030 0.9554 0.0351
-5.250 -0.5645 0.01484 0.00740 -0.0025 0.9546 0.0364
-5.000 -0.5393 0.01453 0.00708 -0.0022 0.9539 0.0382
-4.750 -0.5134 0.01428 0.00681 -0.0020 0.9533 0.0397
-4.500 -0.4868 0.01406 0.00659 -0.0019 0.9528 0.0415
-4.250 -0.4594 0.01386 0.00638 -0.0020 0.9523 0.0434
-4.000 -0.4315 0.01368 0.00618 -0.0022 0.9518 0.0457
-3.750 -0.4236 0.01360 0.00611 0.0022 0.9483 0.0501
-3.500 -0.4063 0.01348 0.00601 0.0044 0.9461 0.0572
-3.250 -0.3848 0.01328 0.00590 0.0056 0.9447 0.0731
-3.000 -0.3618 0.01309 0.00580 0.0065 0.9435 0.0934
-2.750 -0.3375 0.01290 0.00570 0.0071 0.9424 0.1137
-2.500 -0.3123 0.01269 0.00560 0.0074 0.9415 0.1383
-2.250 -0.2871 0.01248 0.00551 0.0078 0.9406 0.1681
-2.000 -0.2623 0.01224 0.00544 0.0082 0.9399 0.2073
-1.750 -0.2384 0.01193 0.00538 0.0088 0.9393 0.2680
-1.500 -0.2156 0.01155 0.00531 0.0096 0.9386 0.3451
-1.000 -0.2069 0.01067 0.00523 0.0197 0.9317 0.5491
-0.500 -0.1241 0.01009 0.00606 0.0143 0.9309 0.9098
-0.250 -0.0682 0.01026 0.00622 0.0083 0.9289 0.9166
0.000 0.0000 0.01008 0.00603 0.0000 0.9253 0.9253
0.250 0.0681 0.01026 0.00622 -0.0083 0.9166 0.9289
0.500 0.1258 0.01007 0.00603 -0.0146 0.9096 0.9307
1.000 0.1723 0.00969 0.00561 -0.0120 0.8639 0.9383
1.500 0.2155 0.01156 0.00531 -0.0096 0.3439 0.9386
1.750 0.2384 0.01193 0.00538 -0.0088 0.2685 0.9393
2.000 0.2623 0.01224 0.00544 -0.0082 0.2070 0.9399
2.250 0.2871 0.01248 0.00551 -0.0078 0.1676 0.9406
2.500 0.3122 0.01269 0.00560 -0.0074 0.1381 0.9415
2.750 0.3374 0.01290 0.00570 -0.0070 0.1139 0.9424
3.000 0.3617 0.01308 0.00580 -0.0065 0.0935 0.9435
3.250 0.3848 0.01328 0.00590 -0.0056 0.0731 0.9447
3.500 0.4062 0.01347 0.00601 -0.0044 0.0573 0.9461
3.750 0.4234 0.01360 0.00611 -0.0022 0.0501 0.9484
4.000 0.4316 0.01368 0.00618 0.0022 0.0457 0.9518
4.250 0.4596 0.01386 0.00638 0.0020 0.0434 0.9523
4.500 0.4869 0.01406 0.00659 0.0019 0.0414 0.9528
4.750 0.5134 0.01428 0.00681 0.0019 0.0397 0.9533
5.000 0.5393 0.01453 0.00708 0.0021 0.0382 0.9539
5.250 0.5645 0.01484 0.00740 0.0025 0.0364 0.9546
5.500 0.5891 0.01516 0.00776 0.0030 0.0351 0.9554
5.750 0.6135 0.01541 0.00806 0.0035 0.0345 0.9563
6.000 0.6370 0.01570 0.00839 0.0043 0.0339 0.9574
6.250 0.6594 0.01597 0.00872 0.0053 0.0329 0.9587
6.500 0.6796 0.01624 0.00903 0.0067 0.0319 0.9605
6.750 0.6860 0.01642 0.00925 0.0114 0.0311 0.9642
7.000 0.7124 0.01674 0.00961 0.0113 0.0300 0.9646
7.250 0.7382 0.01712 0.01001 0.0114 0.0287 0.9651
7.500 0.7619 0.01782 0.01076 0.0119 0.0271 0.9656
7.750 0.7876 0.01810 0.01111 0.0120 0.0264 0.9662
8.000 0.8128 0.01840 0.01148 0.0123 0.0256 0.9669
8.250 0.8373 0.01872 0.01189 0.0127 0.0244 0.9677
8.500 0.8614 0.01900 0.01223 0.0131 0.0231 0.9686
8.750 0.8852 0.01927 0.01253 0.0136 0.0219 0.9698
9.000 0.9065 0.01963 0.01292 0.0146 0.0208 0.9712
9.250 0.9230 0.02010 0.01345 0.0167 0.0199 0.9731
9.500 0.9351 0.02038 0.01383 0.0198 0.0191 0.9755
9.750 0.9604 0.02074 0.01428 0.0199 0.0178 0.9760
10.000 0.9854 0.02106 0.01466 0.0200 0.0166 0.9766
10.250 1.0096 0.02142 0.01503 0.0202 0.0154 0.9772
10.500 1.0315 0.02204 0.01574 0.0209 0.0145 0.9780
10.750 1.0531 0.02268 0.01650 0.0216 0.0137 0.9789
11.000 1.0740 0.02329 0.01721 0.0224 0.0129 0.9801
11.250 1.0929 0.02387 0.01788 0.0237 0.0122 0.9814
11.500 1.1077 0.02449 0.01857 0.0258 0.0115 0.9831
11.750 1.1138 0.02524 0.01941 0.0297 0.0109 0.9855
12.000 1.1315 0.02609 0.02043 0.0309 0.0105 0.9862
12.250 1.1474 0.02701 0.02151 0.0324 0.0100 0.9870
12.500 1.1616 0.02799 0.02264 0.0341 0.0096 0.9880
12.750 1.1748 0.02902 0.02382 0.0359 0.0093 0.9892
13.000 1.1856 0.03010 0.02505 0.0380 0.0090 0.9905
13.250 1.1933 0.03128 0.02638 0.0406 0.0087 0.9920
13.500 1.1976 0.03261 0.02785 0.0436 0.0084 0.9935
13.750 1.1984 0.03424 0.02964 0.0469 0.0082 0.9947
14.000 1.1985 0.03619 0.03178 0.0496 0.0080 0.9956
14.250 1.1988 0.03818 0.03398 0.0520 0.0079 0.9965
14.500 1.1961 0.04051 0.03653 0.0543 0.0078 0.9976
14.750 1.1892 0.04325 0.03949 0.0565 0.0077 0.9986
15.000 1.1779 0.04656 0.04301 0.0583 0.0076 0.9995
15.250 1.1586 0.05049 0.04715 0.0600 0.0075 1.0000
15.500 1.1290 0.05551 0.05235 0.0612 0.0076 1.0000
15.750 1.0733 0.06933 0.06648 0.0527 0.0078 1.0000
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