ONERA NACA CAMBRE AIRFOIL (ncambre-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA NACA CAMBRE AIRFOIL (ncambre-il) Reynolds number: 200,000 Max Cl/Cd: 54.27 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ncambre-il-200000-n5.txt Download as CSV file: xf-ncambre-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5963 0.08957 0.08578 -0.0156 1.0000 0.0256
-10.000 -0.6097 0.08034 0.07656 -0.0233 1.0000 0.0252
-9.750 -0.6336 0.07180 0.06793 -0.0306 1.0000 0.0247
-9.500 -0.6574 0.06614 0.06214 -0.0327 1.0000 0.0244
-9.250 -0.6767 0.06167 0.05751 -0.0318 1.0000 0.0242
-9.000 -0.6890 0.05701 0.05264 -0.0307 1.0000 0.0240
-8.750 -0.6987 0.05204 0.04737 -0.0289 1.0000 0.0237
-8.500 -0.7053 0.04691 0.04185 -0.0265 1.0000 0.0233
-8.250 -0.7051 0.04273 0.03731 -0.0240 1.0000 0.0232
-8.000 -0.6998 0.03947 0.03373 -0.0215 1.0000 0.0232
-7.750 -0.6914 0.03674 0.03070 -0.0192 1.0000 0.0233
-7.500 -0.6808 0.03437 0.02806 -0.0169 1.0000 0.0234
-7.250 -0.6684 0.03221 0.02564 -0.0147 1.0000 0.0236
-7.000 -0.6544 0.03026 0.02343 -0.0126 1.0000 0.0239
-6.750 -0.6390 0.02861 0.02155 -0.0106 1.0000 0.0243
-6.500 -0.6226 0.02712 0.01983 -0.0087 1.0000 0.0251
-6.250 -0.6055 0.02562 0.01807 -0.0068 1.0000 0.0257
-6.000 -0.5874 0.02419 0.01639 -0.0050 1.0000 0.0262
-5.750 -0.5684 0.02292 0.01490 -0.0033 1.0000 0.0265
-5.500 -0.5419 0.02172 0.01349 -0.0031 0.9983 0.0268
-5.250 -0.5056 0.02041 0.01214 -0.0052 0.9942 0.0274
-5.000 -0.4703 0.01944 0.01114 -0.0070 0.9888 0.0281
-4.750 -0.4347 0.01856 0.01023 -0.0087 0.9845 0.0290
-4.500 -0.4018 0.01783 0.00945 -0.0099 0.9790 0.0303
-4.250 -0.3675 0.01717 0.00871 -0.0113 0.9739 0.0319
-4.000 -0.3346 0.01634 0.00791 -0.0125 0.9683 0.0331
-3.750 -0.3034 0.01568 0.00728 -0.0134 0.9606 0.0343
-3.500 -0.2715 0.01509 0.00670 -0.0143 0.9524 0.0359
-3.250 -0.2393 0.01458 0.00615 -0.0152 0.9428 0.0380
-3.000 -0.2098 0.01404 0.00563 -0.0155 0.9299 0.0408
-2.750 -0.1794 0.01361 0.00518 -0.0159 0.9164 0.0439
-2.500 -0.1496 0.01319 0.00473 -0.0162 0.9025 0.0474
-2.250 -0.1201 0.01286 0.00436 -0.0163 0.8887 0.0537
-2.000 -0.0923 0.01247 0.00400 -0.0162 0.8737 0.0657
-1.750 -0.0674 0.01181 0.00364 -0.0156 0.8546 0.1445
-1.500 -0.0543 0.00997 0.00331 -0.0133 0.8336 0.5197
-1.250 -0.0328 0.00950 0.00323 -0.0115 0.8117 0.6348
-1.000 -0.0097 0.00926 0.00320 -0.0099 0.7895 0.7082
-0.750 0.0140 0.00913 0.00324 -0.0082 0.7683 0.7768
-0.500 0.0389 0.00914 0.00331 -0.0067 0.7454 0.8318
-0.250 0.0658 0.00925 0.00337 -0.0056 0.7183 0.8690
0.000 0.0937 0.00939 0.00337 -0.0051 0.6898 0.8907
0.250 0.1236 0.00954 0.00337 -0.0051 0.6643 0.9047
0.500 0.1544 0.00968 0.00338 -0.0054 0.6411 0.9166
1.000 0.2150 0.00997 0.00339 -0.0060 0.5924 0.9379
1.250 0.2473 0.01014 0.00341 -0.0068 0.5690 0.9460
1.500 0.2775 0.01029 0.00345 -0.0072 0.5462 0.9558
1.750 0.3120 0.01048 0.00349 -0.0086 0.5186 0.9615
2.000 0.3437 0.01068 0.00353 -0.0095 0.4905 0.9688
2.250 0.3786 0.01088 0.00359 -0.0110 0.4657 0.9740
2.500 0.4138 0.01107 0.00368 -0.0127 0.4421 0.9797
2.750 0.4501 0.01127 0.00377 -0.0146 0.4168 0.9858
3.000 0.4875 0.01148 0.00386 -0.0168 0.3908 0.9917
3.250 0.5241 0.01171 0.00396 -0.0189 0.3648 0.9966
3.500 0.5564 0.01197 0.00408 -0.0202 0.3406 1.0000
3.750 0.5788 0.01217 0.00422 -0.0193 0.3200 1.0000
4.000 0.6012 0.01239 0.00436 -0.0184 0.3015 1.0000
4.250 0.6234 0.01263 0.00452 -0.0175 0.2853 1.0000
4.500 0.6456 0.01287 0.00470 -0.0165 0.2712 1.0000
4.750 0.6677 0.01313 0.00492 -0.0155 0.2575 1.0000
5.000 0.6897 0.01341 0.00514 -0.0146 0.2441 1.0000
5.250 0.7118 0.01369 0.00537 -0.0136 0.2309 1.0000
5.500 0.7341 0.01396 0.00564 -0.0126 0.2192 1.0000
5.750 0.7562 0.01426 0.00591 -0.0117 0.2089 1.0000
6.000 0.7778 0.01461 0.00621 -0.0106 0.1988 1.0000
6.250 0.8000 0.01491 0.00652 -0.0097 0.1886 1.0000
6.500 0.8218 0.01526 0.00687 -0.0087 0.1793 1.0000
6.750 0.8435 0.01563 0.00722 -0.0077 0.1702 1.0000
7.000 0.8658 0.01597 0.00759 -0.0068 0.1623 1.0000
7.250 0.8873 0.01639 0.00800 -0.0058 0.1550 1.0000
7.500 0.9096 0.01676 0.00843 -0.0049 0.1485 1.0000
7.750 0.9311 0.01721 0.00887 -0.0040 0.1424 1.0000
8.000 0.9529 0.01767 0.00936 -0.0031 0.1368 1.0000
8.250 0.9747 0.01812 0.00986 -0.0022 0.1311 1.0000
8.500 0.9952 0.01868 0.01040 -0.0012 0.1256 1.0000
8.750 1.0177 0.01906 0.01088 -0.0005 0.1185 1.0000
9.000 1.0382 0.01959 0.01139 0.0004 0.1113 1.0000
9.250 1.0603 0.02001 0.01189 0.0011 0.1044 1.0000
9.500 1.0801 0.02059 0.01247 0.0021 0.0991 1.0000
9.750 1.1015 0.02107 0.01306 0.0029 0.0944 1.0000
10.000 1.1213 0.02164 0.01368 0.0038 0.0893 1.0000
10.250 1.1408 0.02224 0.01435 0.0048 0.0845 1.0000
10.500 1.1603 0.02282 0.01502 0.0057 0.0789 1.0000
10.750 1.1781 0.02351 0.01576 0.0069 0.0738 1.0000
11.000 1.1964 0.02415 0.01651 0.0079 0.0676 1.0000
11.250 1.2129 0.02490 0.01733 0.0091 0.0611 1.0000
11.500 1.2274 0.02577 0.01823 0.0105 0.0538 1.0000
12.000 1.2478 0.02783 0.02038 0.0143 0.0414 1.0000
12.250 1.2543 0.02912 0.02172 0.0164 0.0379 1.0000
12.500 1.2598 0.03054 0.02322 0.0182 0.0353 1.0000
12.750 1.2623 0.03226 0.02502 0.0199 0.0334 1.0000
13.000 1.2646 0.03413 0.02700 0.0213 0.0319 1.0000
13.250 1.2665 0.03616 0.02918 0.0222 0.0305 1.0000
13.500 1.2664 0.03854 0.03170 0.0227 0.0293 1.0000
13.750 1.2638 0.04139 0.03468 0.0227 0.0284 1.0000
14.000 1.2581 0.04484 0.03826 0.0221 0.0276 1.0000
14.250 1.2504 0.04881 0.04235 0.0209 0.0270 1.0000
14.500 1.2451 0.05273 0.04644 0.0194 0.0265 1.0000
14.750 1.2373 0.05717 0.05105 0.0176 0.0260 1.0000
15.000 1.2273 0.06208 0.05612 0.0154 0.0257 1.0000
15.250 1.2155 0.06741 0.06160 0.0129 0.0253 1.0000
15.500 1.2021 0.07307 0.06741 0.0102 0.0251 1.0000
15.750 1.1876 0.07902 0.07351 0.0074 0.0248 1.0000
16.000 1.1726 0.08519 0.07982 0.0044 0.0246 1.0000
16.250 1.1574 0.09152 0.08627 0.0014 0.0244 1.0000
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