MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.68 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske1-il-1000000-n5.txt Download as CSV file: xf-marske1-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -1.0997 0.03413 0.02936 -0.0170 0.5865 0.0209
-12.500 -1.1026 0.03264 0.02773 -0.0131 0.5843 0.0210
-12.250 -1.0956 0.03134 0.02629 -0.0105 0.5819 0.0210
-12.000 -1.0836 0.03037 0.02522 -0.0084 0.5798 0.0211
-11.750 -1.0694 0.02951 0.02428 -0.0065 0.5777 0.0212
-11.500 -1.0540 0.02866 0.02335 -0.0047 0.5751 0.0212
-11.250 -1.0374 0.02785 0.02245 -0.0031 0.5722 0.0213
-11.000 -1.0189 0.02725 0.02177 -0.0016 0.5694 0.0214
-10.750 -1.0006 0.02647 0.02090 -0.0002 0.5664 0.0214
-10.500 -0.9813 0.02579 0.02013 0.0012 0.5633 0.0215
-10.250 -0.9608 0.02519 0.01947 0.0024 0.5610 0.0216
-10.000 -0.9402 0.02452 0.01872 0.0037 0.5581 0.0217
-9.750 -0.9195 0.02375 0.01786 0.0048 0.5547 0.0218
-9.500 -0.8985 0.02291 0.01692 0.0060 0.5511 0.0220
-9.250 -0.8766 0.02217 0.01608 0.0071 0.5478 0.0221
-9.000 -0.8550 0.02121 0.01500 0.0082 0.5448 0.0224
-8.750 -0.8326 0.02027 0.01397 0.0092 0.5412 0.0226
-8.500 -0.8099 0.01933 0.01290 0.0101 0.5365 0.0229
-8.250 -0.7865 0.01849 0.01196 0.0110 0.5319 0.0233
-8.000 -0.7628 0.01772 0.01107 0.0119 0.5278 0.0235
-7.750 -0.7385 0.01704 0.01032 0.0127 0.5236 0.0237
-7.500 -0.7140 0.01644 0.00965 0.0135 0.5179 0.0238
-7.250 -0.6891 0.01595 0.00907 0.0142 0.5114 0.0240
-7.000 -0.6646 0.01535 0.00843 0.0150 0.5045 0.0242
-6.750 -0.6394 0.01496 0.00799 0.0157 0.4954 0.0243
-6.500 -0.6136 0.01464 0.00763 0.0164 0.4872 0.0245
-6.250 -0.5878 0.01435 0.00730 0.0170 0.4777 0.0246
-6.000 -0.5617 0.01410 0.00701 0.0176 0.4694 0.0248
-5.750 -0.5356 0.01383 0.00669 0.0182 0.4600 0.0250
-5.500 -0.5094 0.01358 0.00639 0.0188 0.4516 0.0252
-5.250 -0.4832 0.01333 0.00609 0.0193 0.4423 0.0254
-5.000 -0.4571 0.01307 0.00579 0.0199 0.4340 0.0257
-4.750 -0.4310 0.01279 0.00547 0.0205 0.4263 0.0260
-4.250 -0.3786 0.01226 0.00486 0.0217 0.4140 0.0266
-4.000 -0.3523 0.01202 0.00458 0.0223 0.4084 0.0269
-3.750 -0.3258 0.01183 0.00434 0.0228 0.4022 0.0272
-3.500 -0.2994 0.01160 0.00409 0.0233 0.3968 0.0275
-3.250 -0.2726 0.01141 0.00390 0.0238 0.3916 0.0278
-3.000 -0.2456 0.01127 0.00374 0.0243 0.3864 0.0281
-2.750 -0.2186 0.01114 0.00359 0.0247 0.3813 0.0284
-2.500 -0.1914 0.01100 0.00344 0.0251 0.3773 0.0287
-2.250 -0.1643 0.01085 0.00329 0.0255 0.3728 0.0291
-2.000 -0.1372 0.01072 0.00314 0.0260 0.3678 0.0296
-1.750 -0.1101 0.01061 0.00300 0.0264 0.3631 0.0301
-1.500 -0.0828 0.01049 0.00286 0.0268 0.3596 0.0305
-1.250 -0.0555 0.01036 0.00273 0.0271 0.3558 0.0309
-1.000 -0.0282 0.01025 0.00262 0.0275 0.3514 0.0314
-0.750 -0.0007 0.01019 0.00255 0.0278 0.3473 0.0319
-0.500 0.0270 0.01014 0.00250 0.0281 0.3432 0.0326
-0.250 0.0547 0.01007 0.00243 0.0284 0.3404 0.0334
0.000 0.0823 0.00999 0.00235 0.0287 0.3370 0.0341
0.250 0.1099 0.00993 0.00228 0.0290 0.3332 0.0347
0.500 0.1375 0.00988 0.00223 0.0293 0.3296 0.0354
0.750 0.1651 0.00985 0.00220 0.0296 0.3260 0.0362
1.000 0.1930 0.00981 0.00217 0.0298 0.3235 0.0371
1.250 0.2209 0.00978 0.00215 0.0300 0.3211 0.0382
1.500 0.2487 0.00973 0.00212 0.0303 0.3180 0.0393
1.750 0.2765 0.00972 0.00211 0.0305 0.3144 0.0405
2.000 0.3042 0.00972 0.00211 0.0307 0.3108 0.0417
2.250 0.3319 0.00973 0.00212 0.0309 0.3073 0.0429
2.500 0.3599 0.00971 0.00212 0.0311 0.3054 0.0444
2.750 0.3879 0.00971 0.00213 0.0313 0.3031 0.0463
3.000 0.4158 0.00970 0.00214 0.0314 0.3004 0.0483
3.250 0.4436 0.00972 0.00217 0.0316 0.2975 0.0506
3.500 0.4713 0.00974 0.00220 0.0318 0.2944 0.0544
3.750 0.4984 0.00973 0.00226 0.0321 0.2906 0.1004
4.000 0.5259 0.00971 0.00230 0.0322 0.2882 0.1220
4.250 0.5481 0.00917 0.00237 0.0332 0.2854 0.3600
4.500 0.5589 0.00801 0.00234 0.0364 0.2823 0.7399
4.750 0.5808 0.00785 0.00244 0.0378 0.2781 0.8189
5.000 0.6052 0.00783 0.00257 0.0387 0.2740 0.8687
5.250 0.6319 0.00784 0.00270 0.0392 0.2715 0.9031
5.500 0.6609 0.00791 0.00283 0.0392 0.2683 0.9271
5.750 0.6931 0.00803 0.00298 0.0384 0.2637 0.9451
6.000 0.7237 0.00820 0.00313 0.0379 0.2587 0.9542
6.250 0.7594 0.00835 0.00330 0.0363 0.2543 0.9619
6.500 0.7890 0.00849 0.00343 0.0360 0.2497 0.9682
6.750 0.8214 0.00867 0.00359 0.0350 0.2450 0.9707
7.000 0.8541 0.00885 0.00376 0.0339 0.2409 0.9724
7.250 0.8871 0.00900 0.00391 0.0328 0.2371 0.9744
7.500 0.9192 0.00918 0.00409 0.0318 0.2321 0.9773
7.750 0.9470 0.00940 0.00430 0.0317 0.2273 0.9816
8.000 0.9806 0.00958 0.00448 0.0304 0.2231 0.9826
8.250 1.0127 0.00978 0.00468 0.0293 0.2175 0.9837
8.500 1.0439 0.01006 0.00493 0.0283 0.2105 0.9851
8.750 1.0751 0.01027 0.00514 0.0274 0.2039 0.9866
9.000 1.1047 0.01061 0.00544 0.0267 0.1943 0.9884
9.250 1.1332 0.01102 0.00578 0.0261 0.1812 0.9904
9.500 1.1603 0.01148 0.00617 0.0257 0.1673 0.9925
9.750 1.1890 0.01203 0.00665 0.0248 0.1507 0.9940
10.000 1.2178 0.01261 0.00715 0.0238 0.1370 0.9956
10.250 1.2463 0.01318 0.00768 0.0229 0.1266 0.9973
10.500 1.2753 0.01367 0.00815 0.0219 0.1196 0.9987
10.750 1.3038 0.01420 0.00867 0.0210 0.1136 0.9998
11.000 1.3243 0.01465 0.00912 0.0218 0.1092 1.0000
11.250 1.3402 0.01519 0.00966 0.0233 0.1045 1.0000
11.500 1.3573 0.01565 0.01013 0.0247 0.1015 1.0000
11.750 1.3740 0.01611 0.01063 0.0260 0.0985 1.0000
12.000 1.3889 0.01670 0.01122 0.0275 0.0950 1.0000
12.250 1.4023 0.01736 0.01189 0.0291 0.0916 1.0000
12.500 1.4168 0.01794 0.01251 0.0305 0.0890 1.0000
12.750 1.4277 0.01871 0.01331 0.0322 0.0856 1.0000
13.000 1.4316 0.01981 0.01442 0.0343 0.0821 1.0000
13.250 1.4272 0.02159 0.01629 0.0359 0.0802 1.0000
13.500 1.4280 0.02438 0.01916 0.0344 0.0776 1.0000
13.750 1.4252 0.02717 0.02199 0.0338 0.0748 1.0000
14.000 1.4197 0.03009 0.02495 0.0334 0.0723 1.0000
14.250 1.4166 0.03276 0.02768 0.0332 0.0703 1.0000
14.500 1.4107 0.03574 0.03071 0.0328 0.0680 1.0000
14.750 1.3995 0.03930 0.03432 0.0322 0.0653 1.0000
15.000 1.3913 0.04268 0.03775 0.0316 0.0634 1.0000
15.250 1.3829 0.04615 0.04129 0.0308 0.0613 1.0000
15.500 1.3735 0.04986 0.04506 0.0299 0.0593 1.0000
15.750 1.3626 0.05393 0.04917 0.0288 0.0573 1.0000
16.000 1.3553 0.05765 0.05296 0.0277 0.0556 1.0000
16.250 1.3476 0.06150 0.05687 0.0265 0.0541 1.0000
16.500 1.3382 0.06560 0.06103 0.0252 0.0524 1.0000
16.750 1.3295 0.06963 0.06511 0.0239 0.0509 1.0000
17.000 1.3208 0.07377 0.06930 0.0225 0.0493 1.0000
17.250 1.3149 0.07759 0.07317 0.0212 0.0482 1.0000
17.500 1.3086 0.08146 0.07710 0.0199 0.0465 1.0000
17.750 1.3010 0.08562 0.08131 0.0184 0.0456 1.0000
18.000 1.2938 0.08970 0.08543 0.0169 0.0442 1.0000
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Polar data table (+)
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