NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NPL 9626 AIRFOIL (npl9626-il) Reynolds number: 100,000 Max Cl/Cd: 39.86 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9626-il-100000-n5.txt Download as CSV file: xf-npl9626-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6848 0.10792 0.10235 -0.0083 1.0000 0.0289
-12.250 -0.7105 0.09608 0.09050 -0.0151 1.0000 0.0286
-12.000 -0.7433 0.08375 0.07809 -0.0240 1.0000 0.0282
-11.750 -0.7744 0.07395 0.06811 -0.0317 1.0000 0.0278
-11.500 -0.8019 0.06669 0.06064 -0.0366 1.0000 0.0276
-11.250 -0.8261 0.06120 0.05492 -0.0387 1.0000 0.0276
-11.000 -0.8472 0.05687 0.05034 -0.0385 1.0000 0.0276
-10.750 -0.8651 0.05330 0.04649 -0.0364 1.0000 0.0277
-10.500 -0.8773 0.04981 0.04267 -0.0339 1.0000 0.0279
-10.250 -0.8837 0.04632 0.03874 -0.0316 1.0000 0.0283
-10.000 -0.8854 0.04289 0.03481 -0.0292 1.0000 0.0288
-9.750 -0.8753 0.04082 0.03258 -0.0277 1.0000 0.0294
-9.500 -0.8621 0.03935 0.03100 -0.0264 1.0000 0.0304
-9.250 -0.8492 0.03772 0.02916 -0.0249 1.0000 0.0319
-9.000 -0.8377 0.03550 0.02646 -0.0230 1.0000 0.0337
-8.750 -0.8204 0.03435 0.02534 -0.0220 1.0000 0.0351
-8.500 -0.8031 0.03295 0.02378 -0.0207 1.0000 0.0367
-8.250 -0.7857 0.03128 0.02173 -0.0191 1.0000 0.0389
-8.000 -0.7669 0.03011 0.02061 -0.0181 1.0000 0.0405
-7.750 -0.7475 0.02888 0.01928 -0.0169 1.0000 0.0424
-7.500 -0.7273 0.02750 0.01770 -0.0156 1.0000 0.0443
-7.250 -0.7079 0.02627 0.01645 -0.0143 1.0000 0.0460
-7.000 -0.6889 0.02527 0.01545 -0.0129 1.0000 0.0481
-6.750 -0.6698 0.02431 0.01440 -0.0114 1.0000 0.0506
-6.500 -0.6515 0.02340 0.01347 -0.0099 1.0000 0.0535
-6.250 -0.6330 0.02270 0.01277 -0.0084 1.0000 0.0577
-6.000 -0.6147 0.02196 0.01202 -0.0069 1.0000 0.0627
-5.750 -0.5965 0.02126 0.01131 -0.0053 1.0000 0.0677
-5.500 -0.5788 0.02049 0.01052 -0.0036 1.0000 0.0721
-5.250 -0.5607 0.01981 0.00984 -0.0020 1.0000 0.0785
-5.000 -0.5427 0.01910 0.00916 -0.0004 1.0000 0.0861
-4.750 -0.5241 0.01844 0.00851 0.0011 1.0000 0.0970
-4.500 -0.5055 0.01772 0.00791 0.0026 1.0000 0.1171
-4.250 -0.4879 0.01680 0.00739 0.0039 1.0000 0.1712
-4.000 -0.4703 0.01596 0.00707 0.0052 1.0000 0.2691
-3.750 -0.4512 0.01545 0.00687 0.0065 1.0000 0.3449
-3.500 -0.4127 0.01491 0.00670 0.0039 0.9912 0.4302
-3.250 -0.3744 0.01448 0.00659 0.0017 0.9819 0.5028
-3.000 -0.3380 0.01414 0.00652 0.0001 0.9722 0.5696
-2.750 -0.3041 0.01387 0.00651 -0.0008 0.9620 0.6355
-2.500 -0.2680 0.01370 0.00647 -0.0020 0.9527 0.6850
-2.250 -0.2318 0.01358 0.00640 -0.0032 0.9425 0.7196
-2.000 -0.1981 0.01349 0.00635 -0.0038 0.9301 0.7502
-1.750 -0.1635 0.01344 0.00630 -0.0045 0.9177 0.7790
-1.500 -0.1285 0.01340 0.00626 -0.0053 0.9050 0.8064
-1.250 -0.0922 0.01338 0.00623 -0.0063 0.8913 0.8300
-1.000 -0.0576 0.01338 0.00619 -0.0069 0.8749 0.8518
-0.750 -0.0228 0.01338 0.00613 -0.0077 0.8574 0.8714
-0.500 0.0121 0.01340 0.00609 -0.0084 0.8386 0.8888
-0.250 0.0475 0.01343 0.00605 -0.0094 0.8185 0.9041
0.000 0.0837 0.01347 0.00601 -0.0105 0.7966 0.9180
0.250 0.1199 0.01351 0.00596 -0.0116 0.7738 0.9309
0.500 0.1554 0.01357 0.00592 -0.0127 0.7502 0.9434
0.750 0.1928 0.01364 0.00589 -0.0144 0.7260 0.9542
1.000 0.2324 0.01371 0.00584 -0.0165 0.7020 0.9627
1.250 0.2694 0.01379 0.00583 -0.0183 0.6776 0.9724
1.500 0.3088 0.01389 0.00582 -0.0206 0.6543 0.9821
1.750 0.3511 0.01397 0.00582 -0.0235 0.6323 0.9915
2.000 0.3926 0.01406 0.00585 -0.0265 0.6115 1.0000
2.250 0.4156 0.01416 0.00588 -0.0257 0.5946 1.0000
2.500 0.4387 0.01428 0.00596 -0.0249 0.5794 1.0000
2.750 0.4617 0.01443 0.00605 -0.0241 0.5646 1.0000
3.000 0.4846 0.01458 0.00616 -0.0232 0.5489 1.0000
3.250 0.5070 0.01475 0.00629 -0.0222 0.5313 1.0000
3.500 0.5288 0.01492 0.00641 -0.0210 0.5093 1.0000
3.750 0.5496 0.01511 0.00649 -0.0197 0.4816 1.0000
4.000 0.5698 0.01532 0.00658 -0.0182 0.4487 1.0000
4.250 0.5904 0.01555 0.00672 -0.0169 0.4182 1.0000
4.500 0.6117 0.01581 0.00692 -0.0157 0.3949 1.0000
4.750 0.6329 0.01607 0.00717 -0.0145 0.3673 1.0000
5.000 0.6533 0.01639 0.00742 -0.0131 0.3283 1.0000
5.250 0.6714 0.01693 0.00769 -0.0115 0.2595 1.0000
5.500 0.6850 0.01811 0.00826 -0.0096 0.1634 1.0000
5.750 0.6999 0.01927 0.00908 -0.0078 0.1179 1.0000
6.000 0.7167 0.02018 0.00985 -0.0061 0.1008 1.0000
6.250 0.7343 0.02096 0.01063 -0.0045 0.0914 1.0000
6.500 0.7519 0.02174 0.01144 -0.0029 0.0850 1.0000
6.750 0.7694 0.02252 0.01223 -0.0014 0.0793 1.0000
7.000 0.7863 0.02335 0.01308 0.0002 0.0750 1.0000
7.250 0.8041 0.02412 0.01391 0.0017 0.0709 1.0000
7.500 0.8207 0.02502 0.01479 0.0033 0.0676 1.0000
7.750 0.8380 0.02595 0.01576 0.0048 0.0648 1.0000
8.000 0.8560 0.02684 0.01673 0.0061 0.0618 1.0000
8.250 0.8735 0.02781 0.01770 0.0074 0.0592 1.0000
8.500 0.8909 0.02903 0.01884 0.0087 0.0573 1.0000
8.750 0.9105 0.03017 0.02013 0.0098 0.0555 1.0000
9.000 0.9298 0.03139 0.02148 0.0109 0.0535 1.0000
9.250 0.9484 0.03260 0.02275 0.0119 0.0515 1.0000
9.500 0.9669 0.03391 0.02402 0.0128 0.0497 1.0000
9.750 0.9854 0.03552 0.02576 0.0137 0.0482 1.0000
10.000 1.0025 0.03721 0.02770 0.0149 0.0469 1.0000
10.250 1.0178 0.03888 0.02958 0.0161 0.0454 1.0000
10.500 1.0316 0.04040 0.03124 0.0174 0.0438 1.0000
10.750 1.0452 0.04187 0.03276 0.0185 0.0425 1.0000
11.000 1.0557 0.04383 0.03486 0.0198 0.0413 1.0000
11.250 1.0580 0.04604 0.03746 0.0220 0.0402 1.0000
11.500 1.0572 0.04824 0.03996 0.0244 0.0392 1.0000
11.750 1.0547 0.05054 0.04249 0.0265 0.0384 1.0000
12.000 1.0512 0.05299 0.04516 0.0282 0.0378 1.0000
12.250 1.0458 0.05574 0.04812 0.0295 0.0373 1.0000
12.500 1.0383 0.05882 0.05141 0.0301 0.0370 1.0000
12.750 1.0284 0.06232 0.05512 0.0302 0.0367 1.0000
13.000 1.0152 0.06642 0.05942 0.0294 0.0365 1.0000
13.250 0.9981 0.07132 0.06455 0.0277 0.0363 1.0000
13.500 0.9752 0.07751 0.07098 0.0245 0.0363 1.0000
13.750 0.9366 0.08696 0.08074 0.0185 0.0366 1.0000
14.000 0.7925 0.12419 0.11845 -0.0068 0.0387 1.0000
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