NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.52 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9660-il-1000000.txt Download as CSV file: xf-npl9660-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9660 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -1.0584 0.04633 0.04383 -0.0317 1.0000 0.0143
-12.750 -1.1096 0.03847 0.03546 -0.0304 1.0000 0.0142
-12.500 -1.1267 0.03468 0.03135 -0.0276 1.0000 0.0141
-12.250 -1.1282 0.03193 0.02833 -0.0255 1.0000 0.0141
-12.000 -1.1224 0.02948 0.02562 -0.0239 1.0000 0.0141
-11.750 -1.1121 0.02734 0.02325 -0.0226 1.0000 0.0141
-11.500 -1.0984 0.02549 0.02120 -0.0214 1.0000 0.0141
-11.250 -1.0821 0.02388 0.01940 -0.0205 1.0000 0.0140
-11.000 -1.0638 0.02248 0.01783 -0.0197 1.0000 0.0140
-10.750 -1.0441 0.02124 0.01644 -0.0190 1.0000 0.0140
-10.500 -1.0233 0.02013 0.01521 -0.0184 1.0000 0.0140
-10.250 -1.0017 0.01913 0.01410 -0.0178 1.0000 0.0140
-10.000 -0.9796 0.01825 0.01311 -0.0172 1.0000 0.0140
-9.750 -0.9569 0.01752 0.01231 -0.0167 1.0000 0.0140
-9.500 -0.9345 0.01685 0.01156 -0.0161 1.0000 0.0141
-9.250 -0.9140 0.01616 0.01080 -0.0150 1.0000 0.0141
-9.000 -0.8939 0.01553 0.01010 -0.0139 0.9996 0.0141
-8.750 -0.8640 0.01485 0.00935 -0.0147 0.9970 0.0140
-8.500 -0.8335 0.01423 0.00866 -0.0156 0.9947 0.0140
-8.250 -0.8023 0.01366 0.00804 -0.0166 0.9923 0.0140
-8.000 -0.7706 0.01314 0.00748 -0.0177 0.9896 0.0140
-7.750 -0.7388 0.01267 0.00697 -0.0187 0.9866 0.0141
-7.500 -0.7081 0.01226 0.00652 -0.0195 0.9832 0.0141
-7.250 -0.6818 0.01194 0.00616 -0.0193 0.9788 0.0141
-7.000 -0.6573 0.01170 0.00588 -0.0186 0.9737 0.0142
-6.750 -0.6339 0.01149 0.00565 -0.0177 0.9689 0.0143
-6.500 -0.6110 0.01128 0.00541 -0.0166 0.9637 0.0143
-6.250 -0.5884 0.01111 0.00521 -0.0154 0.9590 0.0145
-6.000 -0.5636 0.01086 0.00494 -0.0148 0.9540 0.0146
-5.750 -0.5407 0.01066 0.00472 -0.0136 0.9492 0.0148
-5.500 -0.5145 0.01040 0.00445 -0.0132 0.9447 0.0151
-5.250 -0.4892 0.01015 0.00419 -0.0125 0.9396 0.0155
-5.000 -0.4648 0.00991 0.00395 -0.0117 0.9357 0.0165
-4.750 -0.4376 0.00968 0.00371 -0.0115 0.9310 0.0182
-4.500 -0.4116 0.00943 0.00347 -0.0110 0.9260 0.0201
-4.250 -0.3864 0.00921 0.00326 -0.0103 0.9215 0.0233
-4.000 -0.3591 0.00902 0.00310 -0.0101 0.9157 0.0271
-3.750 -0.3324 0.00886 0.00292 -0.0097 0.9087 0.0291
-3.500 -0.3059 0.00869 0.00275 -0.0093 0.9012 0.0311
-3.250 -0.2786 0.00854 0.00259 -0.0090 0.8911 0.0324
-3.000 -0.2511 0.00841 0.00244 -0.0088 0.8812 0.0335
-2.750 -0.2237 0.00828 0.00228 -0.0086 0.8701 0.0346
-2.500 -0.1957 0.00815 0.00215 -0.0085 0.8572 0.0363
-2.250 -0.1681 0.00805 0.00202 -0.0084 0.8417 0.0378
-2.000 -0.1402 0.00798 0.00190 -0.0083 0.8245 0.0395
-1.750 -0.1122 0.00790 0.00179 -0.0082 0.8057 0.0423
-1.500 -0.0841 0.00786 0.00170 -0.0082 0.7826 0.0455
-1.250 -0.0560 0.00783 0.00161 -0.0082 0.7568 0.0503
-1.000 -0.0276 0.00781 0.00153 -0.0082 0.7319 0.0576
-0.750 0.0008 0.00775 0.00147 -0.0084 0.7112 0.0737
-0.500 0.0261 0.00648 0.00120 -0.0088 0.6902 0.3950
-0.250 0.0532 0.00595 0.00113 -0.0090 0.6672 0.5461
0.000 0.0813 0.00576 0.00111 -0.0092 0.6410 0.6187
0.500 0.1373 0.00557 0.00111 -0.0093 0.5862 0.7350
0.750 0.1647 0.00548 0.00117 -0.0091 0.5664 0.7939
1.000 0.1920 0.00549 0.00124 -0.0089 0.5488 0.8326
1.250 0.2188 0.00555 0.00134 -0.0084 0.5311 0.8600
1.500 0.2459 0.00567 0.00143 -0.0081 0.5118 0.8800
1.750 0.2729 0.00579 0.00152 -0.0078 0.4941 0.8936
2.000 0.2995 0.00594 0.00163 -0.0073 0.4770 0.9070
2.250 0.3242 0.00615 0.00180 -0.0063 0.4601 0.9210
2.500 0.3490 0.00633 0.00193 -0.0055 0.4427 0.9268
2.750 0.3759 0.00650 0.00204 -0.0052 0.4245 0.9316
3.000 0.4036 0.00667 0.00214 -0.0051 0.4042 0.9358
3.250 0.4289 0.00685 0.00224 -0.0045 0.3796 0.9394
3.500 0.4547 0.00710 0.00236 -0.0040 0.3488 0.9439
3.750 0.4821 0.00740 0.00252 -0.0041 0.3131 0.9482
4.000 0.5058 0.00762 0.00261 -0.0032 0.2817 0.9519
4.250 0.5305 0.00789 0.00274 -0.0026 0.2499 0.9563
4.500 0.5567 0.00814 0.00290 -0.0023 0.2264 0.9602
4.750 0.5796 0.00831 0.00296 -0.0013 0.2009 0.9644
5.000 0.6038 0.00852 0.00307 -0.0006 0.1794 0.9690
5.250 0.6283 0.00868 0.00315 0.0000 0.1607 0.9732
5.500 0.6540 0.00885 0.00326 0.0004 0.1467 0.9774
5.750 0.6806 0.00903 0.00339 0.0005 0.1354 0.9815
6.000 0.7110 0.00925 0.00356 -0.0002 0.1245 0.9852
6.250 0.7435 0.00949 0.00376 -0.0014 0.1145 0.9882
6.500 0.7759 0.00975 0.00398 -0.0027 0.1051 0.9905
6.750 0.8073 0.01003 0.00421 -0.0037 0.0956 0.9923
7.000 0.8392 0.01033 0.00445 -0.0048 0.0821 0.9941
7.250 0.8714 0.01069 0.00474 -0.0061 0.0690 0.9961
7.500 0.9020 0.01120 0.00515 -0.0072 0.0514 0.9984
7.750 0.9283 0.01176 0.00561 -0.0073 0.0358 1.0000
8.000 0.9488 0.01219 0.00601 -0.0062 0.0300 1.0000
8.250 0.9720 0.01256 0.00637 -0.0056 0.0273 1.0000
8.500 0.9961 0.01298 0.00680 -0.0052 0.0252 1.0000
8.750 1.0212 0.01335 0.00719 -0.0050 0.0238 1.0000
9.000 1.0459 0.01381 0.00766 -0.0048 0.0224 1.0000
9.250 1.0704 0.01430 0.00818 -0.0045 0.0213 1.0000
9.500 1.0955 0.01471 0.00863 -0.0044 0.0203 1.0000
9.750 1.1200 0.01519 0.00913 -0.0042 0.0193 1.0000
10.000 1.1420 0.01595 0.00993 -0.0037 0.0182 1.0000
10.250 1.1659 0.01646 0.01049 -0.0034 0.0176 1.0000
10.500 1.1893 0.01699 0.01108 -0.0031 0.0170 1.0000
10.750 1.2119 0.01758 0.01171 -0.0027 0.0164 1.0000
11.000 1.2338 0.01822 0.01239 -0.0022 0.0159 1.0000
11.250 1.2535 0.01903 0.01325 -0.0015 0.0154 1.0000
11.500 1.2678 0.02029 0.01459 -0.0002 0.0149 1.0000
11.750 1.2858 0.02112 0.01550 0.0007 0.0147 1.0000
12.000 1.3039 0.02188 0.01633 0.0016 0.0145 1.0000
12.250 1.3193 0.02271 0.01723 0.0028 0.0143 1.0000
12.500 1.3314 0.02364 0.01824 0.0044 0.0141 1.0000
12.750 1.3424 0.02468 0.01936 0.0060 0.0140 1.0000
13.000 1.3531 0.02577 0.02053 0.0074 0.0138 1.0000
13.250 1.3628 0.02697 0.02182 0.0088 0.0136 1.0000
13.500 1.3714 0.02831 0.02324 0.0100 0.0134 1.0000
13.750 1.3781 0.02987 0.02488 0.0111 0.0133 1.0000
14.000 1.3835 0.03164 0.02674 0.0119 0.0131 1.0000
14.250 1.3878 0.03363 0.02882 0.0125 0.0130 1.0000
14.500 1.3908 0.03588 0.03117 0.0128 0.0129 1.0000
14.750 1.3923 0.03845 0.03384 0.0128 0.0129 1.0000
15.000 1.3925 0.04132 0.03681 0.0123 0.0128 1.0000
15.250 1.3910 0.04455 0.04015 0.0116 0.0127 1.0000
15.500 1.3881 0.04809 0.04380 0.0105 0.0127 1.0000
15.750 1.3834 0.05200 0.04781 0.0092 0.0126 1.0000
16.000 1.3771 0.05625 0.05217 0.0075 0.0126 1.0000
16.250 1.3690 0.06080 0.05684 0.0057 0.0125 1.0000
16.500 1.3597 0.06566 0.06182 0.0036 0.0125 1.0000
16.750 1.3490 0.07086 0.06712 0.0013 0.0125 1.0000
17.000 1.3374 0.07629 0.07267 -0.0012 0.0125 1.0000
17.250 1.3250 0.08202 0.07851 -0.0038 0.0125 1.0000
17.500 1.3120 0.08793 0.08454 -0.0067 0.0124 1.0000
17.750 1.2982 0.09413 0.09085 -0.0097 0.0124 1.0000
18.000 1.2843 0.10048 0.09732 -0.0129 0.0124 1.0000
18.250 1.2701 0.10696 0.10391 -0.0161 0.0124 1.0000
18.500 1.2556 0.11367 0.11074 -0.0196 0.0124 1.0000
18.750 1.2403 0.12070 0.11788 -0.0234 0.0124 1.0000
19.000 1.2254 0.12776 0.12505 -0.0272 0.0124 1.0000
19.250 1.2097 0.13515 0.13257 -0.0314 0.0125 1.0000
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