NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 500,000 Max Cl/Cd: 89.93 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca25112-jf-500000.txt Download as CSV file: xf-naca25112-jf-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 25112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7670 0.06133 0.05888 -0.0291 1.0000 0.0229
-11.250 -0.8119 0.05246 0.04977 -0.0328 1.0000 0.0227
-11.000 -0.8650 0.04447 0.04134 -0.0298 1.0000 0.0225
-10.750 -0.8978 0.03722 0.03342 -0.0260 1.0000 0.0227
-10.500 -0.9011 0.03346 0.02913 -0.0232 1.0000 0.0229
-10.250 -0.8989 0.02982 0.02515 -0.0208 1.0000 0.0233
-10.000 -0.8810 0.02869 0.02397 -0.0197 1.0000 0.0238
-9.750 -0.8610 0.02791 0.02315 -0.0188 1.0000 0.0242
-9.500 -0.8408 0.02709 0.02226 -0.0178 1.0000 0.0248
-9.250 -0.8227 0.02571 0.02069 -0.0165 1.0000 0.0254
-9.000 -0.8052 0.02408 0.01879 -0.0150 1.0000 0.0261
-8.750 -0.7861 0.02269 0.01714 -0.0136 1.0000 0.0267
-8.500 -0.7666 0.02134 0.01553 -0.0122 1.0000 0.0272
-8.250 -0.7464 0.01999 0.01413 -0.0111 1.0000 0.0279
-8.000 -0.7245 0.01935 0.01348 -0.0101 1.0000 0.0286
-7.750 -0.7028 0.01880 0.01288 -0.0089 1.0000 0.0294
-7.500 -0.6819 0.01822 0.01222 -0.0076 1.0000 0.0304
-7.250 -0.6616 0.01766 0.01154 -0.0061 1.0000 0.0313
-7.000 -0.6325 0.01652 0.01030 -0.0065 0.9968 0.0324
-6.750 -0.5949 0.01581 0.00960 -0.0088 0.9903 0.0336
-6.500 -0.5579 0.01525 0.00900 -0.0107 0.9804 0.0351
-6.250 -0.5223 0.01478 0.00844 -0.0122 0.9663 0.0367
-6.000 -0.4911 0.01396 0.00759 -0.0128 0.9460 0.0384
-5.750 -0.4637 0.01360 0.00720 -0.0125 0.9205 0.0401
-5.500 -0.4397 0.01330 0.00679 -0.0113 0.8916 0.0418
-5.250 -0.4154 0.01309 0.00643 -0.0102 0.8623 0.0433
-5.000 -0.3926 0.01254 0.00581 -0.0089 0.8347 0.0457
-4.750 -0.3675 0.01236 0.00554 -0.0081 0.8077 0.0482
-4.500 -0.3418 0.01220 0.00523 -0.0074 0.7818 0.0504
-4.250 -0.3175 0.01177 0.00473 -0.0066 0.7570 0.0536
-4.000 -0.2914 0.01163 0.00450 -0.0060 0.7339 0.0571
-3.750 -0.2657 0.01137 0.00414 -0.0054 0.7113 0.0608
-3.500 -0.2396 0.01119 0.00390 -0.0049 0.6898 0.0652
-3.250 -0.2131 0.01104 0.00365 -0.0045 0.6699 0.0701
-2.750 -0.1604 0.01068 0.00320 -0.0036 0.6333 0.0838
-2.500 -0.1335 0.01058 0.00304 -0.0033 0.6168 0.0921
-2.250 -0.1070 0.01041 0.00286 -0.0029 0.6014 0.1037
-2.000 -0.0802 0.01026 0.00271 -0.0026 0.5867 0.1181
-1.750 -0.0533 0.01012 0.00258 -0.0024 0.5734 0.1372
-1.500 -0.0268 0.00993 0.00247 -0.0020 0.5614 0.1678
-1.000 0.0133 0.00818 0.00211 0.0004 0.5400 0.5660
-0.750 0.0280 0.00735 0.00213 0.0035 0.5312 0.7965
-0.500 0.0531 0.00729 0.00227 0.0049 0.5214 0.8772
-0.250 0.0813 0.00743 0.00241 0.0054 0.5122 0.9122
0.000 0.1112 0.00762 0.00255 0.0055 0.5030 0.9330
0.250 0.1426 0.00782 0.00269 0.0053 0.4945 0.9472
0.750 0.2182 0.00828 0.00299 0.0018 0.4769 0.9641
1.000 0.2560 0.00850 0.00311 -0.0001 0.4685 0.9712
1.250 0.3039 0.00868 0.00323 -0.0042 0.4596 0.9747
1.500 0.3468 0.00889 0.00335 -0.0072 0.4513 0.9809
1.750 0.3976 0.00904 0.00346 -0.0119 0.4425 0.9866
2.000 0.4369 0.00914 0.00348 -0.0144 0.4347 0.9900
2.250 0.4709 0.00918 0.00350 -0.0158 0.4274 0.9928
2.500 0.5061 0.00923 0.00349 -0.0174 0.4198 0.9947
2.750 0.5420 0.00926 0.00350 -0.0192 0.4126 0.9965
3.000 0.5775 0.00929 0.00350 -0.0210 0.4049 0.9985
3.250 0.6114 0.00936 0.00353 -0.0224 0.3979 1.0000
3.500 0.6368 0.00939 0.00356 -0.0220 0.3909 1.0000
3.750 0.6620 0.00950 0.00360 -0.0216 0.3842 1.0000
4.000 0.6875 0.00952 0.00365 -0.0213 0.3775 1.0000
4.250 0.7127 0.00961 0.00371 -0.0209 0.3706 1.0000
4.500 0.7381 0.00968 0.00379 -0.0205 0.3639 1.0000
4.750 0.7632 0.00977 0.00386 -0.0200 0.3567 1.0000
5.000 0.7881 0.00988 0.00397 -0.0196 0.3499 1.0000
5.250 0.8128 0.00997 0.00406 -0.0190 0.3424 1.0000
5.500 0.8370 0.01012 0.00418 -0.0184 0.3352 1.0000
5.750 0.8615 0.01021 0.00431 -0.0179 0.3275 1.0000
6.000 0.8854 0.01038 0.00445 -0.0172 0.3197 1.0000
6.250 0.9096 0.01050 0.00459 -0.0166 0.3111 1.0000
6.500 0.9332 0.01067 0.00475 -0.0159 0.3027 1.0000
6.750 0.9567 0.01083 0.00491 -0.0152 0.2934 1.0000
7.000 0.9801 0.01101 0.00509 -0.0144 0.2843 1.0000
7.250 1.0028 0.01125 0.00530 -0.0136 0.2745 1.0000
7.500 1.0260 0.01142 0.00550 -0.0128 0.2644 1.0000
7.750 1.0486 0.01166 0.00573 -0.0120 0.2542 1.0000
8.000 1.0705 0.01194 0.00599 -0.0110 0.2434 1.0000
8.250 1.0925 0.01221 0.00626 -0.0101 0.2317 1.0000
8.500 1.1142 0.01251 0.00654 -0.0092 0.2196 1.0000
8.750 1.1353 0.01285 0.00686 -0.0081 0.2069 1.0000
9.000 1.1558 0.01323 0.00722 -0.0070 0.1933 1.0000
9.250 1.1757 0.01366 0.00761 -0.0059 0.1789 1.0000
9.500 1.1949 0.01415 0.00804 -0.0046 0.1636 1.0000
9.750 1.2131 0.01470 0.00853 -0.0033 0.1476 1.0000
10.000 1.2300 0.01534 0.00910 -0.0018 0.1314 1.0000
10.250 1.2467 0.01598 0.00969 -0.0003 0.1158 1.0000
10.500 1.2624 0.01670 0.01034 0.0013 0.1010 1.0000
10.750 1.2772 0.01748 0.01106 0.0030 0.0876 1.0000
11.000 1.2913 0.01830 0.01185 0.0046 0.0763 1.0000
11.250 1.3047 0.01915 0.01268 0.0064 0.0672 1.0000
11.500 1.3166 0.02006 0.01358 0.0082 0.0601 1.0000
11.750 1.3262 0.02105 0.01456 0.0102 0.0544 1.0000
12.000 1.3342 0.02194 0.01551 0.0126 0.0503 1.0000
12.250 1.3382 0.02318 0.01676 0.0149 0.0467 1.0000
12.500 1.3445 0.02445 0.01810 0.0166 0.0438 1.0000
12.750 1.3500 0.02596 0.01967 0.0177 0.0413 1.0000
13.000 1.3491 0.02823 0.02200 0.0185 0.0391 1.0000
13.250 1.3545 0.03019 0.02405 0.0187 0.0374 1.0000
13.500 1.3585 0.03246 0.02642 0.0186 0.0357 1.0000
13.750 1.3578 0.03538 0.02941 0.0180 0.0343 1.0000
14.000 1.3501 0.03927 0.03338 0.0171 0.0331 1.0000
14.250 1.3501 0.04234 0.03657 0.0163 0.0321 1.0000
14.500 1.3486 0.04560 0.03993 0.0155 0.0311 1.0000
14.750 1.3447 0.04918 0.04361 0.0145 0.0303 1.0000
15.000 1.3382 0.05309 0.04760 0.0134 0.0295 1.0000
15.250 1.3288 0.05734 0.05193 0.0122 0.0289 1.0000
15.500 1.3161 0.06201 0.05667 0.0109 0.0283 1.0000
15.750 1.3025 0.06684 0.06157 0.0096 0.0278 1.0000
16.000 1.2986 0.07065 0.06550 0.0084 0.0273 1.0000
16.250 1.2932 0.07468 0.06964 0.0072 0.0267 1.0000
16.500 1.2875 0.07882 0.07387 0.0058 0.0261 1.0000
16.750 1.2818 0.08302 0.07815 0.0044 0.0255 1.0000
17.000 1.2761 0.08726 0.08245 0.0029 0.0250 1.0000
17.250 1.2697 0.09162 0.08688 0.0013 0.0245 1.0000
17.500 1.2626 0.09608 0.09138 -0.0003 0.0240 1.0000
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