NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NPL 9626 AIRFOIL (npl9626-il) Reynolds number: 50,000 Max Cl/Cd: 29.82 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9626-il-50000.txt Download as CSV file: xf-npl9626-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9626 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5893 0.09922 0.09198 -0.0040 1.0000 0.2299
-9.000 -0.7056 0.07576 0.06849 -0.0261 1.0000 0.1517
-8.750 -0.7041 0.07044 0.06310 -0.0263 1.0000 0.1456
-8.500 -0.7535 0.06273 0.05463 -0.0263 1.0000 0.1353
-8.250 -0.7445 0.05815 0.04995 -0.0255 1.0000 0.1334
-8.000 -0.7413 0.05374 0.04525 -0.0241 1.0000 0.1313
-7.750 -0.7374 0.04958 0.04067 -0.0223 1.0000 0.1297
-7.500 -0.7294 0.04589 0.03655 -0.0204 1.0000 0.1295
-7.250 -0.7185 0.04273 0.03294 -0.0185 1.0000 0.1315
-7.000 -0.7058 0.03992 0.02956 -0.0164 1.0000 0.1344
-6.750 -0.6874 0.03725 0.02678 -0.0151 1.0000 0.1397
-6.500 -0.6681 0.03513 0.02442 -0.0136 1.0000 0.1465
-6.250 -0.6477 0.03290 0.02197 -0.0122 1.0000 0.1536
-6.000 -0.6245 0.03098 0.01992 -0.0110 1.0000 0.1617
-5.750 -0.6009 0.02916 0.01810 -0.0099 1.0000 0.1729
-5.500 -0.5761 0.02745 0.01641 -0.0088 1.0000 0.1869
-5.250 -0.5526 0.02591 0.01497 -0.0075 1.0000 0.2096
-5.000 -0.5315 0.02427 0.01370 -0.0059 1.0000 0.2481
-4.750 -0.5193 0.02225 0.01267 -0.0029 1.0000 0.3525
-4.500 -0.5173 0.02104 0.01258 0.0034 1.0000 0.5210
-4.250 -0.5070 0.02103 0.01290 0.0089 1.0000 0.6080
-4.000 -0.4928 0.02117 0.01317 0.0136 1.0000 0.6689
-3.750 -0.4761 0.02138 0.01342 0.0180 1.0000 0.7192
-3.500 -0.4577 0.02198 0.01406 0.0231 1.0000 0.7702
-3.250 -0.4225 0.02340 0.01543 0.0272 1.0000 0.8255
-3.000 -0.3566 0.02432 0.01600 0.0235 1.0000 0.8685
-2.750 -0.2732 0.02458 0.01585 0.0144 1.0000 0.9047
-2.500 -0.1793 0.02433 0.01520 0.0020 1.0000 0.9390
-2.250 -0.0892 0.02357 0.01412 -0.0109 1.0000 0.9713
-2.000 0.0034 0.02233 0.01262 -0.0251 1.0000 1.0000
-1.750 0.0057 0.02173 0.01203 -0.0233 1.0000 1.0000
-1.500 0.0040 0.02128 0.01160 -0.0206 1.0000 1.0000
-1.250 -0.0018 0.02098 0.01132 -0.0170 1.0000 1.0000
-1.000 -0.0128 0.02083 0.01119 -0.0126 1.0000 1.0000
-0.750 -0.0279 0.02082 0.01118 -0.0075 1.0000 1.0000
-0.500 -0.0436 0.02095 0.01128 -0.0024 1.0000 1.0000
-0.250 -0.0563 0.02120 0.01150 0.0021 1.0000 1.0000
0.000 -0.0640 0.02160 0.01183 0.0057 1.0000 1.0000
0.250 -0.0669 0.02212 0.01228 0.0084 1.0000 1.0000
0.500 0.0042 0.02305 0.01318 -0.0019 0.9791 1.0000
0.750 0.0760 0.02382 0.01394 -0.0118 0.9573 1.0000
1.000 0.1371 0.02437 0.01451 -0.0193 0.9333 1.0000
1.250 0.2033 0.02477 0.01497 -0.0272 0.9118 1.0000
1.500 0.2734 0.02493 0.01524 -0.0354 0.8920 1.0000
1.750 0.3176 0.02518 0.01555 -0.0387 0.8696 1.0000
2.000 0.3586 0.02540 0.01584 -0.0411 0.8487 1.0000
2.250 0.3961 0.02562 0.01612 -0.0427 0.8294 1.0000
2.500 0.4283 0.02591 0.01648 -0.0433 0.8111 1.0000
2.750 0.4566 0.02626 0.01690 -0.0431 0.7935 1.0000
3.000 0.4819 0.02671 0.01742 -0.0425 0.7766 1.0000
3.250 0.5053 0.02722 0.01800 -0.0415 0.7600 1.0000
3.500 0.5275 0.02778 0.01865 -0.0404 0.7438 1.0000
3.750 0.5494 0.02836 0.01931 -0.0391 0.7278 1.0000
4.000 0.5712 0.02890 0.01995 -0.0376 0.7114 1.0000
4.250 0.5941 0.02924 0.02040 -0.0358 0.6931 1.0000
4.500 0.6237 0.02823 0.01941 -0.0323 0.6645 1.0000
4.750 0.6472 0.02681 0.01791 -0.0271 0.6250 1.0000
5.000 0.6688 0.02583 0.01684 -0.0227 0.5879 1.0000
5.250 0.6889 0.02554 0.01655 -0.0195 0.5570 1.0000
5.500 0.7081 0.02518 0.01617 -0.0161 0.5211 1.0000
5.750 0.7239 0.02472 0.01566 -0.0119 0.4720 1.0000
6.000 0.7293 0.02446 0.01495 -0.0059 0.3778 1.0000
6.250 0.7312 0.02579 0.01536 -0.0008 0.2696 1.0000
6.500 0.7469 0.02755 0.01663 0.0014 0.2271 1.0000
6.750 0.7675 0.02921 0.01793 0.0028 0.2037 1.0000
7.000 0.7918 0.03093 0.01954 0.0037 0.1879 1.0000
7.250 0.8160 0.03267 0.02125 0.0046 0.1753 1.0000
7.500 0.8391 0.03460 0.02339 0.0055 0.1659 1.0000
7.750 0.8637 0.03679 0.02550 0.0061 0.1579 1.0000
8.000 0.8821 0.03900 0.02812 0.0075 0.1520 1.0000
8.250 0.9033 0.04141 0.03067 0.0084 0.1471 1.0000
8.500 0.9211 0.04432 0.03375 0.0095 0.1430 1.0000
8.750 0.9300 0.04728 0.03726 0.0115 0.1404 1.0000
9.000 0.9370 0.05074 0.04117 0.0133 0.1394 1.0000
9.250 0.9396 0.05458 0.04544 0.0152 0.1393 1.0000
9.500 0.9367 0.05875 0.05000 0.0170 0.1395 1.0000
9.750 0.9270 0.06324 0.05484 0.0187 0.1401 1.0000
10.000 0.9116 0.06805 0.05993 0.0201 0.1411 1.0000
10.250 0.8940 0.07310 0.06516 0.0209 0.1423 1.0000
10.500 0.8780 0.07812 0.07029 0.0214 0.1434 1.0000
10.750 0.7520 0.09838 0.09067 0.0064 0.1606 1.0000
11.000 0.6958 0.11614 0.10826 -0.0065 0.1873 1.0000
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Polar data table (+)
Polar graphs
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