MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 500,000 Max Cl/Cd: 88.79 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske1-il-500000-n5.txt Download as CSV file: xf-marske1-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MARSKE XM-1D AIRFOIL (F14-3.0)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5727 0.08913 0.08536 0.0009 0.5773 0.0234
-10.750 -0.7171 0.05762 0.05356 -0.0202 0.5832 0.0232
-10.500 -0.7639 0.05201 0.04769 -0.0171 0.5824 0.0233
-10.250 -0.8068 0.04704 0.04235 -0.0113 0.5814 0.0236
-10.000 -0.8373 0.04140 0.03615 -0.0061 0.5804 0.0240
-9.750 -0.8291 0.03964 0.03426 -0.0041 0.5775 0.0241
-9.500 -0.8180 0.03808 0.03257 -0.0023 0.5744 0.0242
-9.250 -0.8047 0.03665 0.03100 -0.0007 0.5708 0.0244
-9.000 -0.7907 0.03516 0.02936 0.0010 0.5673 0.0245
-8.750 -0.7746 0.03389 0.02795 0.0025 0.5639 0.0246
-8.500 -0.7579 0.03253 0.02643 0.0039 0.5606 0.0247
-8.250 -0.7405 0.03116 0.02491 0.0054 0.5568 0.0249
-8.000 -0.7220 0.02984 0.02343 0.0067 0.5527 0.0251
-7.750 -0.7030 0.02851 0.02192 0.0081 0.5485 0.0253
-7.500 -0.6830 0.02722 0.02043 0.0094 0.5444 0.0256
-7.250 -0.6621 0.02592 0.01897 0.0106 0.5397 0.0258
-7.000 -0.6403 0.02465 0.01751 0.0117 0.5347 0.0261
-6.750 -0.6178 0.02339 0.01603 0.0128 0.5300 0.0267
-6.500 -0.5945 0.02191 0.01429 0.0138 0.5251 0.0271
-6.250 -0.5699 0.02085 0.01309 0.0146 0.5186 0.0274
-6.000 -0.5447 0.02023 0.01240 0.0152 0.5115 0.0275
-5.750 -0.5191 0.01965 0.01176 0.0158 0.5041 0.0277
-5.500 -0.4934 0.01911 0.01116 0.0164 0.4959 0.0279
-5.250 -0.4674 0.01861 0.01059 0.0169 0.4884 0.0282
-5.000 -0.4411 0.01808 0.01000 0.0174 0.4799 0.0284
-4.750 -0.4147 0.01757 0.00940 0.0179 0.4719 0.0287
-4.500 -0.3881 0.01703 0.00881 0.0184 0.4631 0.0291
-4.250 -0.3616 0.01652 0.00821 0.0189 0.4545 0.0294
-4.000 -0.3349 0.01601 0.00763 0.0194 0.4463 0.0299
-3.750 -0.3083 0.01554 0.00707 0.0199 0.4385 0.0305
-3.500 -0.2818 0.01511 0.00660 0.0204 0.4323 0.0309
-3.250 -0.2553 0.01479 0.00627 0.0209 0.4258 0.0312
-3.000 -0.2288 0.01451 0.00596 0.0214 0.4194 0.0316
-2.750 -0.2023 0.01422 0.00566 0.0218 0.4137 0.0319
-2.500 -0.1758 0.01394 0.00537 0.0223 0.4076 0.0324
-2.250 -0.1495 0.01368 0.00507 0.0229 0.4019 0.0328
-2.000 -0.1232 0.01342 0.00479 0.0234 0.3974 0.0334
-1.750 -0.0968 0.01316 0.00452 0.0240 0.3928 0.0340
-1.500 -0.0704 0.01295 0.00428 0.0245 0.3875 0.0345
-1.250 -0.0443 0.01275 0.00407 0.0250 0.3826 0.0350
-1.000 -0.0175 0.01261 0.00394 0.0255 0.3784 0.0358
-0.750 0.0093 0.01245 0.00379 0.0259 0.3745 0.0366
-0.500 0.0360 0.01230 0.00363 0.0264 0.3700 0.0374
-0.250 0.0627 0.01218 0.00349 0.0268 0.3655 0.0382
0.000 0.0890 0.01205 0.00334 0.0273 0.3612 0.0389
0.250 0.1159 0.01191 0.00324 0.0277 0.3581 0.0397
0.500 0.1429 0.01181 0.00315 0.0281 0.3546 0.0406
0.750 0.1702 0.01175 0.00309 0.0285 0.3506 0.0420
1.000 0.1970 0.01167 0.00301 0.0289 0.3465 0.0432
1.250 0.2239 0.01164 0.00295 0.0292 0.3427 0.0445
1.500 0.2513 0.01158 0.00291 0.0295 0.3399 0.0458
1.750 0.2787 0.01153 0.00288 0.0298 0.3368 0.0472
2.000 0.3059 0.01150 0.00285 0.0301 0.3336 0.0493
2.250 0.3332 0.01150 0.00284 0.0304 0.3302 0.0515
2.500 0.3603 0.01150 0.00282 0.0307 0.3266 0.0542
2.750 0.3876 0.01151 0.00284 0.0310 0.3235 0.0581
3.000 0.4143 0.01142 0.00288 0.0314 0.3206 0.1089
3.250 0.4383 0.01108 0.00293 0.0321 0.3177 0.2484
3.500 0.4469 0.00967 0.00285 0.0355 0.3152 0.6839
3.750 0.4655 0.00931 0.00299 0.0377 0.3124 0.8119
4.000 0.4918 0.00929 0.00317 0.0384 0.3094 0.8768
4.250 0.5219 0.00940 0.00334 0.0383 0.3065 0.9078
4.500 0.5580 0.00953 0.00353 0.0368 0.3037 0.9303
4.750 0.5934 0.00968 0.00371 0.0355 0.3001 0.9446
5.000 0.6274 0.00986 0.00389 0.0344 0.2962 0.9566
5.250 0.6658 0.01007 0.00406 0.0323 0.2919 0.9620
5.500 0.6967 0.01025 0.00424 0.0318 0.2883 0.9691
5.750 0.7328 0.01038 0.00439 0.0301 0.2844 0.9709
6.000 0.7670 0.01054 0.00454 0.0287 0.2797 0.9728
6.250 0.8008 0.01073 0.00471 0.0275 0.2755 0.9755
6.500 0.8331 0.01091 0.00489 0.0265 0.2715 0.9793
6.750 0.8644 0.01106 0.00506 0.0257 0.2668 0.9822
7.000 0.8976 0.01123 0.00523 0.0245 0.2616 0.9837
7.250 0.9299 0.01144 0.00542 0.0234 0.2576 0.9855
7.500 0.9620 0.01160 0.00562 0.0224 0.2542 0.9875
7.750 0.9931 0.01178 0.00582 0.0215 0.2498 0.9897
8.000 1.0231 0.01200 0.00605 0.0209 0.2447 0.9919
8.250 1.0541 0.01224 0.00629 0.0199 0.2403 0.9937
8.500 1.0863 0.01243 0.00652 0.0188 0.2352 0.9954
8.750 1.1175 0.01269 0.00678 0.0178 0.2293 0.9972
9.000 1.1485 0.01297 0.00707 0.0167 0.2234 0.9989
9.250 1.1774 0.01326 0.00737 0.0161 0.2158 1.0000
9.500 1.1972 0.01362 0.00772 0.0172 0.2087 1.0000
9.750 1.2169 0.01397 0.00807 0.0184 0.1997 1.0000
10.000 1.2357 0.01440 0.00848 0.0196 0.1904 1.0000
10.250 1.2533 0.01490 0.00896 0.0209 0.1802 1.0000
10.500 1.2704 0.01544 0.00947 0.0222 0.1689 1.0000
10.750 1.2863 0.01605 0.01006 0.0236 0.1578 1.0000
11.000 1.3002 0.01679 0.01076 0.0252 0.1463 1.0000
11.250 1.3130 0.01758 0.01152 0.0268 0.1372 1.0000
11.500 1.3246 0.01841 0.01235 0.0285 0.1298 1.0000
11.750 1.3356 0.01925 0.01321 0.0301 0.1243 1.0000
12.000 1.3436 0.02024 0.01422 0.0319 0.1192 1.0000
12.500 1.3385 0.02370 0.01782 0.0351 0.1123 1.0000
12.750 1.3361 0.02637 0.02055 0.0345 0.1093 1.0000
13.000 1.3315 0.02910 0.02333 0.0344 0.1064 1.0000
13.250 1.3247 0.03201 0.02629 0.0342 0.1038 1.0000
13.500 1.3214 0.03464 0.02898 0.0341 0.1017 1.0000
13.750 1.3186 0.03727 0.03168 0.0339 0.0993 1.0000
14.000 1.3135 0.04020 0.03467 0.0336 0.0970 1.0000
14.250 1.3057 0.04349 0.03801 0.0330 0.0945 1.0000
14.500 1.2964 0.04702 0.04159 0.0323 0.0923 1.0000
14.750 1.2921 0.05011 0.04475 0.0317 0.0902 1.0000
15.000 1.2884 0.05327 0.04797 0.0309 0.0879 1.0000
15.250 1.2821 0.05685 0.05160 0.0299 0.0851 1.0000
15.500 1.2743 0.06066 0.05546 0.0288 0.0827 1.0000
15.750 1.2693 0.06419 0.05904 0.0277 0.0802 1.0000
16.000 1.2653 0.06764 0.06256 0.0266 0.0778 1.0000
16.250 1.2591 0.07141 0.06637 0.0254 0.0752 1.0000
16.500 1.2509 0.07551 0.07050 0.0240 0.0728 1.0000
16.750 1.2472 0.07905 0.07410 0.0229 0.0707 1.0000
17.000 1.2434 0.08263 0.07772 0.0217 0.0682 1.0000
17.250 1.2366 0.08669 0.08182 0.0202 0.0660 1.0000
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