NPL 9660 AIRFOIL (npl9660-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9660 AIRFOIL (npl9660-il) Reynolds number: 200,000 Max Cl/Cd: 51.54 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9660-il-200000-n5.txt Download as CSV file: xf-npl9660-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6698 0.08439 0.08070 -0.0132 1.0000 0.0202
-10.250 -0.7172 0.06850 0.06465 -0.0271 1.0000 0.0196
-10.000 -0.7555 0.06034 0.05624 -0.0298 1.0000 0.0193
-9.750 -0.7997 0.05072 0.04613 -0.0287 1.0000 0.0189
-9.500 -0.8371 0.03933 0.03382 -0.0256 1.0000 0.0186
-9.250 -0.8338 0.03511 0.02911 -0.0239 1.0000 0.0187
-9.000 -0.8224 0.03227 0.02592 -0.0226 1.0000 0.0189
-8.750 -0.8074 0.03004 0.02340 -0.0214 1.0000 0.0191
-8.500 -0.7905 0.02814 0.02124 -0.0203 1.0000 0.0193
-8.250 -0.7726 0.02648 0.01935 -0.0191 1.0000 0.0196
-8.000 -0.7543 0.02498 0.01763 -0.0178 1.0000 0.0200
-7.750 -0.7361 0.02361 0.01606 -0.0164 1.0000 0.0204
-7.500 -0.7182 0.02234 0.01460 -0.0149 1.0000 0.0210
-7.250 -0.7003 0.02125 0.01338 -0.0133 1.0000 0.0216
-7.000 -0.6813 0.02073 0.01282 -0.0119 1.0000 0.0221
-6.750 -0.6622 0.02018 0.01222 -0.0105 1.0000 0.0229
-6.500 -0.6432 0.01952 0.01149 -0.0090 1.0000 0.0240
-6.250 -0.6241 0.01883 0.01071 -0.0076 1.0000 0.0253
-6.000 -0.5912 0.01834 0.01018 -0.0090 0.9961 0.0271
-5.750 -0.5571 0.01769 0.00942 -0.0105 0.9923 0.0297
-5.500 -0.5229 0.01725 0.00894 -0.0121 0.9887 0.0321
-5.250 -0.4869 0.01683 0.00846 -0.0141 0.9857 0.0351
-5.000 -0.4502 0.01641 0.00801 -0.0162 0.9829 0.0377
-4.750 -0.4165 0.01599 0.00755 -0.0176 0.9784 0.0401
-4.500 -0.3818 0.01564 0.00719 -0.0193 0.9742 0.0425
-4.250 -0.3475 0.01530 0.00681 -0.0208 0.9697 0.0450
-4.000 -0.3175 0.01496 0.00648 -0.0214 0.9632 0.0470
-3.750 -0.2887 0.01468 0.00619 -0.0217 0.9561 0.0493
-3.500 -0.2606 0.01443 0.00592 -0.0217 0.9486 0.0517
-3.250 -0.2362 0.01414 0.00562 -0.0210 0.9386 0.0541
-3.000 -0.2106 0.01385 0.00535 -0.0206 0.9298 0.0572
-2.750 -0.1842 0.01359 0.00507 -0.0201 0.9217 0.0609
-2.500 -0.1591 0.01330 0.00479 -0.0195 0.9119 0.0647
-2.250 -0.1332 0.01302 0.00451 -0.0189 0.9034 0.0696
-2.000 -0.1078 0.01276 0.00425 -0.0182 0.8913 0.0764
-1.750 -0.0824 0.01245 0.00400 -0.0175 0.8791 0.0916
-1.500 -0.0645 0.01067 0.00355 -0.0165 0.8665 0.4122
-1.250 -0.0433 0.00989 0.00342 -0.0152 0.8527 0.5725
-1.000 -0.0212 0.00944 0.00339 -0.0134 0.8382 0.6739
-0.750 0.0007 0.00921 0.00342 -0.0114 0.8232 0.7443
-0.500 0.0219 0.00917 0.00354 -0.0089 0.8066 0.8026
-0.250 0.0429 0.00926 0.00366 -0.0064 0.7865 0.8452
0.000 0.0641 0.00942 0.00377 -0.0039 0.7645 0.8761
0.250 0.0868 0.00957 0.00382 -0.0020 0.7435 0.8972
0.500 0.1118 0.00968 0.00382 -0.0009 0.7242 0.9090
0.750 0.1372 0.00979 0.00379 0.0000 0.7041 0.9188
1.000 0.1642 0.00990 0.00379 0.0005 0.6830 0.9260
1.250 0.1899 0.01001 0.00379 0.0012 0.6610 0.9353
1.500 0.2177 0.01011 0.00377 0.0015 0.6356 0.9427
1.750 0.2440 0.01024 0.00374 0.0020 0.6085 0.9509
2.000 0.2711 0.01034 0.00372 0.0022 0.5824 0.9588
2.250 0.3027 0.01045 0.00370 0.0015 0.5578 0.9640
2.500 0.3333 0.01056 0.00370 0.0009 0.5340 0.9700
2.750 0.3681 0.01068 0.00374 -0.0006 0.5088 0.9739
3.000 0.4031 0.01083 0.00380 -0.0022 0.4848 0.9778
3.250 0.4361 0.01100 0.00386 -0.0034 0.4613 0.9824
3.500 0.4730 0.01117 0.00396 -0.0055 0.4354 0.9849
3.750 0.5091 0.01139 0.00409 -0.0075 0.4080 0.9877
4.000 0.5442 0.01162 0.00423 -0.0092 0.3781 0.9912
4.250 0.5789 0.01190 0.00441 -0.0110 0.3467 0.9951
4.500 0.6131 0.01224 0.00462 -0.0127 0.3108 0.9993
4.750 0.6369 0.01260 0.00484 -0.0123 0.2787 1.0000
5.000 0.6584 0.01298 0.00509 -0.0114 0.2510 1.0000
5.250 0.6797 0.01335 0.00539 -0.0104 0.2301 1.0000
5.500 0.7011 0.01370 0.00568 -0.0095 0.2117 1.0000
5.750 0.7221 0.01408 0.00600 -0.0084 0.1957 1.0000
6.000 0.7429 0.01448 0.00633 -0.0074 0.1799 1.0000
6.250 0.7635 0.01488 0.00668 -0.0063 0.1626 1.0000
6.500 0.7844 0.01529 0.00703 -0.0053 0.1464 1.0000
6.750 0.8060 0.01569 0.00741 -0.0045 0.1339 1.0000
7.000 0.8283 0.01609 0.00780 -0.0037 0.1240 1.0000
7.250 0.8509 0.01651 0.00822 -0.0031 0.1134 1.0000
7.500 0.8736 0.01698 0.00867 -0.0025 0.1023 1.0000
7.750 0.8965 0.01746 0.00915 -0.0020 0.0901 1.0000
8.000 0.9194 0.01797 0.00964 -0.0015 0.0751 1.0000
8.250 0.9409 0.01866 0.01028 -0.0009 0.0634 1.0000
8.500 0.9621 0.01940 0.01100 -0.0002 0.0526 1.0000
8.750 0.9827 0.02021 0.01178 0.0005 0.0450 1.0000
9.000 1.0031 0.02102 0.01260 0.0012 0.0397 1.0000
9.250 1.0233 0.02182 0.01345 0.0019 0.0359 1.0000
9.500 1.0427 0.02268 0.01438 0.0027 0.0335 1.0000
9.750 1.0616 0.02356 0.01533 0.0035 0.0317 1.0000
10.000 1.0784 0.02457 0.01640 0.0045 0.0302 1.0000
10.250 1.0952 0.02555 0.01749 0.0055 0.0290 1.0000
10.500 1.1109 0.02656 0.01861 0.0066 0.0278 1.0000
10.750 1.1251 0.02764 0.01977 0.0078 0.0267 1.0000
11.000 1.1350 0.02886 0.02104 0.0094 0.0258 1.0000
11.250 1.1450 0.03010 0.02240 0.0110 0.0250 1.0000
11.500 1.1549 0.03140 0.02383 0.0124 0.0242 1.0000
11.750 1.1635 0.03284 0.02538 0.0137 0.0235 1.0000
12.000 1.1707 0.03443 0.02708 0.0149 0.0230 1.0000
12.250 1.1769 0.03617 0.02892 0.0158 0.0225 1.0000
12.500 1.1817 0.03811 0.03094 0.0166 0.0221 1.0000
12.750 1.1852 0.04028 0.03318 0.0172 0.0218 1.0000
13.000 1.1882 0.04262 0.03563 0.0176 0.0215 1.0000
13.250 1.1910 0.04511 0.03830 0.0177 0.0212 1.0000
13.500 1.1926 0.04785 0.04122 0.0175 0.0209 1.0000
13.750 1.1928 0.05084 0.04438 0.0171 0.0206 1.0000
14.000 1.1916 0.05412 0.04783 0.0164 0.0204 1.0000
14.250 1.1889 0.05770 0.05158 0.0153 0.0202 1.0000
14.500 1.1848 0.06159 0.05563 0.0140 0.0200 1.0000
14.750 1.1791 0.06583 0.06004 0.0123 0.0198 1.0000
15.000 1.1718 0.07042 0.06480 0.0102 0.0197 1.0000
15.250 1.1627 0.07545 0.07000 0.0079 0.0196 1.0000
15.500 1.1519 0.08093 0.07565 0.0051 0.0195 1.0000
15.750 1.1393 0.08694 0.08184 0.0019 0.0194 1.0000
16.000 1.1246 0.09359 0.08866 -0.0018 0.0194 1.0000
16.250 1.1073 0.10102 0.09628 -0.0061 0.0194 1.0000
16.500 1.0868 0.10948 0.10494 -0.0111 0.0194 1.0000
16.750 1.0608 0.11964 0.11531 -0.0173 0.0194 1.0000
17.000 1.0203 0.13403 0.12996 -0.0261 0.0196 1.0000
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