ONERA NACA CAMBRE AIRFOIL (ncambre-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA NACA CAMBRE AIRFOIL (ncambre-il) Reynolds number: 200,000 Max Cl/Cd: 52.91 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ncambre-il-200000.txt Download as CSV file: xf-ncambre-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA NACA CAMBRE 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5863 0.09278 0.08910 -0.0217 1.0000 0.0567
-9.750 -0.6133 0.08569 0.08193 -0.0293 1.0000 0.0569
-9.500 -0.6411 0.08174 0.07785 -0.0305 1.0000 0.0570
-9.250 -0.6644 0.07855 0.07444 -0.0301 1.0000 0.0572
-9.000 -0.6764 0.07253 0.06830 -0.0300 1.0000 0.0578
-8.750 -0.6531 0.06760 0.06360 -0.0304 1.0000 0.0589
-8.500 -0.6446 0.06466 0.06068 -0.0298 1.0000 0.0599
-8.250 -0.6398 0.06177 0.05775 -0.0290 1.0000 0.0612
-8.000 -0.6373 0.05878 0.05465 -0.0280 1.0000 0.0630
-7.750 -0.6495 0.05831 0.05348 -0.0244 1.0000 0.0683
-7.500 -0.6488 0.05244 0.04755 -0.0232 1.0000 0.0700
-7.250 -0.6337 0.04942 0.04467 -0.0225 1.0000 0.0717
-7.000 -0.6224 0.04730 0.04253 -0.0209 1.0000 0.0743
-6.500 -0.6115 0.04261 0.03732 -0.0157 1.0000 0.0838
-6.250 -0.5978 0.04043 0.03517 -0.0141 1.0000 0.0864
-5.750 -0.5785 0.03659 0.03093 -0.0092 1.0000 0.0986
-5.500 -0.5639 0.03489 0.02921 -0.0074 1.0000 0.1031
-5.250 -0.5538 0.03314 0.02725 -0.0050 1.0000 0.1134
-5.000 -0.5383 0.03186 0.02592 -0.0032 1.0000 0.1202
-4.750 -0.5053 0.02571 0.01823 0.0018 1.0000 0.0563
-4.500 -0.4849 0.02343 0.01581 0.0031 1.0000 0.0543
-4.250 -0.4632 0.02177 0.01396 0.0045 1.0000 0.0526
-4.000 -0.4412 0.02051 0.01254 0.0058 1.0000 0.0519
-3.750 -0.4168 0.01947 0.01141 0.0064 0.9995 0.0520
-3.500 -0.3751 0.01846 0.01033 0.0037 0.9953 0.0536
-3.250 -0.3332 0.01766 0.00948 0.0009 0.9902 0.0560
-3.000 -0.2892 0.01682 0.00862 -0.0022 0.9848 0.0574
-2.750 -0.2496 0.01552 0.00742 -0.0048 0.9775 0.0607
-2.500 -0.2047 0.01483 0.00679 -0.0083 0.9715 0.0667
-2.250 -0.1671 0.01408 0.00608 -0.0104 0.9625 0.0739
-2.000 -0.1228 0.01341 0.00545 -0.0137 0.9572 0.0919
-1.750 -0.1064 0.01042 0.00493 -0.0123 0.9460 0.6377
-1.500 -0.0782 0.00992 0.00504 -0.0108 0.9351 0.7940
-1.250 -0.0447 0.00986 0.00511 -0.0102 0.9246 0.8567
-1.000 -0.0146 0.00989 0.00514 -0.0092 0.9106 0.8932
-0.750 0.0207 0.01008 0.00530 -0.0090 0.8964 0.9203
-0.500 0.0645 0.01038 0.00552 -0.0105 0.8810 0.9439
-0.250 0.1037 0.01039 0.00541 -0.0120 0.8605 0.9558
0.000 0.1501 0.01038 0.00527 -0.0153 0.8360 0.9617
0.250 0.1889 0.01038 0.00512 -0.0171 0.8123 0.9715
0.500 0.2313 0.01038 0.00498 -0.0199 0.7848 0.9786
0.750 0.2717 0.01038 0.00484 -0.0223 0.7567 0.9863
1.000 0.3125 0.01040 0.00469 -0.0249 0.7268 0.9936
1.250 0.3546 0.01040 0.00451 -0.0279 0.6948 0.9993
1.500 0.3797 0.01044 0.00437 -0.0276 0.6654 1.0000
1.750 0.4028 0.01049 0.00427 -0.0268 0.6358 1.0000
2.000 0.4262 0.01056 0.00420 -0.0261 0.6069 1.0000
2.250 0.4496 0.01066 0.00416 -0.0254 0.5796 1.0000
2.750 0.4961 0.01093 0.00417 -0.0239 0.5261 1.0000
3.000 0.5188 0.01110 0.00422 -0.0231 0.4995 1.0000
3.250 0.5412 0.01133 0.00428 -0.0221 0.4730 1.0000
3.500 0.5636 0.01153 0.00438 -0.0212 0.4457 1.0000
3.750 0.5858 0.01175 0.00451 -0.0202 0.4200 1.0000
4.000 0.6078 0.01200 0.00464 -0.0192 0.3953 1.0000
4.250 0.6297 0.01227 0.00480 -0.0182 0.3721 1.0000
4.500 0.6514 0.01258 0.00500 -0.0171 0.3504 1.0000
4.750 0.6730 0.01292 0.00524 -0.0161 0.3309 1.0000
5.000 0.6946 0.01326 0.00549 -0.0150 0.3130 1.0000
5.250 0.7163 0.01359 0.00576 -0.0139 0.2955 1.0000
5.500 0.7378 0.01395 0.00606 -0.0128 0.2792 1.0000
5.750 0.7592 0.01435 0.00639 -0.0118 0.2639 1.0000
6.000 0.7806 0.01477 0.00675 -0.0107 0.2498 1.0000
6.250 0.8020 0.01518 0.00712 -0.0096 0.2365 1.0000
6.500 0.8237 0.01558 0.00753 -0.0085 0.2238 1.0000
6.750 0.8451 0.01604 0.00797 -0.0074 0.2120 1.0000
7.000 0.8662 0.01657 0.00845 -0.0064 0.2015 1.0000
7.250 0.8877 0.01709 0.00893 -0.0053 0.1919 1.0000
7.500 0.9096 0.01762 0.00952 -0.0044 0.1831 1.0000
7.750 0.9312 0.01829 0.01010 -0.0035 0.1757 1.0000
8.000 0.9536 0.01879 0.01072 -0.0026 0.1686 1.0000
8.250 0.9754 0.01939 0.01127 -0.0017 0.1621 1.0000
8.500 0.9972 0.01989 0.01188 -0.0008 0.1550 1.0000
8.750 1.0181 0.02039 0.01231 0.0000 0.1474 1.0000
9.000 1.0393 0.02079 0.01286 0.0009 0.1401 1.0000
9.250 1.0599 0.02136 0.01339 0.0018 0.1338 1.0000
9.500 1.0808 0.02192 0.01409 0.0027 0.1280 1.0000
9.750 1.1010 0.02241 0.01464 0.0036 0.1222 1.0000
10.000 1.1205 0.02313 0.01541 0.0046 0.1166 1.0000
10.250 1.1398 0.02355 0.01597 0.0057 0.1102 1.0000
10.500 1.1574 0.02426 0.01671 0.0068 0.1041 1.0000
10.750 1.1749 0.02471 0.01730 0.0081 0.0969 1.0000
11.000 1.1901 0.02544 0.01813 0.0095 0.0889 1.0000
11.250 1.2023 0.02629 0.01899 0.0112 0.0800 1.0000
11.500 1.2118 0.02728 0.01999 0.0132 0.0710 1.0000
11.750 1.2205 0.02827 0.02111 0.0154 0.0631 1.0000
12.000 1.2251 0.02971 0.02260 0.0179 0.0578 1.0000
12.250 1.2310 0.03104 0.02400 0.0198 0.0537 1.0000
12.500 1.2334 0.03285 0.02585 0.0217 0.0507 1.0000
12.750 1.2386 0.03450 0.02765 0.0231 0.0478 1.0000
13.000 1.2419 0.03634 0.02955 0.0242 0.0457 1.0000
13.250 1.2411 0.03879 0.03197 0.0253 0.0439 1.0000
13.500 1.2436 0.04107 0.03445 0.0259 0.0426 1.0000
13.750 1.2448 0.04357 0.03712 0.0263 0.0413 1.0000
14.000 1.2452 0.04624 0.03991 0.0264 0.0401 1.0000
14.250 1.2452 0.04903 0.04280 0.0262 0.0391 1.0000
14.500 1.2449 0.05192 0.04574 0.0260 0.0381 1.0000
14.750 1.2439 0.05500 0.04883 0.0263 0.0371 1.0000
15.000 1.2383 0.05879 0.05283 0.0252 0.0365 1.0000
15.250 1.2312 0.06293 0.05718 0.0238 0.0360 1.0000
15.500 1.2226 0.06737 0.06182 0.0221 0.0354 1.0000
15.750 1.2124 0.07220 0.06684 0.0201 0.0350 1.0000
16.000 1.2002 0.07748 0.07231 0.0177 0.0347 1.0000
16.250 1.1861 0.08328 0.07829 0.0148 0.0344 1.0000
16.500 1.1695 0.08975 0.08495 0.0114 0.0342 1.0000
16.750 1.1495 0.09709 0.09249 0.0074 0.0342 1.0000
17.000 1.1247 0.10574 0.10136 0.0023 0.0343 1.0000
17.250 1.0889 0.11719 0.11304 -0.0047 0.0346 1.0000
17.500 1.0268 0.13560 0.13172 -0.0163 0.0358 1.0000
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