MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| 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: 115.31 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske1-il-1000000.txt Download as CSV file: xf-marske1-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6148 0.07802 0.07498 -0.0125 0.5917 0.0281
-11.000 -0.6559 0.06973 0.06656 -0.0187 0.5914 0.0281
-10.750 -0.6869 0.06504 0.06175 -0.0195 0.5900 0.0281
-10.500 -0.7189 0.06156 0.05812 -0.0172 0.5883 0.0281
-10.250 -0.7451 0.05897 0.05541 -0.0128 0.5863 0.0281
-10.000 -0.7809 0.05249 0.04870 -0.0091 0.5850 0.0283
-9.750 -0.7709 0.05006 0.04628 -0.0081 0.5828 0.0285
-9.500 -0.7631 0.04799 0.04417 -0.0065 0.5805 0.0286
-9.250 -0.7536 0.04613 0.04226 -0.0050 0.5778 0.0287
-9.000 -0.7422 0.04451 0.04058 -0.0036 0.5747 0.0288
-8.750 -0.7322 0.04265 0.03863 -0.0019 0.5716 0.0290
-8.500 -0.7217 0.04077 0.03661 -0.0002 0.5680 0.0292
-8.250 -0.7096 0.03895 0.03467 0.0015 0.5650 0.0294
-8.000 -0.6963 0.03714 0.03274 0.0032 0.5620 0.0298
-7.750 -0.6829 0.03522 0.03066 0.0050 0.5586 0.0303
-7.500 -0.6773 0.03505 0.02978 0.0096 0.5554 0.0319
-7.250 -0.6614 0.03342 0.02791 0.0114 0.5517 0.0320
-7.000 -0.6441 0.03177 0.02603 0.0131 0.5476 0.0320
-6.750 -0.6278 0.02704 0.02124 0.0140 0.5441 0.0325
-6.500 -0.6043 0.02574 0.01992 0.0146 0.5389 0.0328
-6.250 -0.5805 0.02469 0.01883 0.0152 0.5334 0.0331
-6.000 -0.5566 0.02377 0.01785 0.0160 0.5280 0.0336
-5.750 -0.5354 0.02156 0.01523 0.0180 0.5228 0.0313
-5.500 -0.5110 0.02017 0.01371 0.0188 0.5162 0.0309
-5.250 -0.4858 0.01900 0.01240 0.0196 0.5096 0.0307
-5.000 -0.4599 0.01798 0.01125 0.0203 0.5015 0.0307
-4.750 -0.4336 0.01710 0.01024 0.0209 0.4927 0.0308
-4.500 -0.4066 0.01637 0.00940 0.0214 0.4831 0.0311
-4.250 -0.3798 0.01590 0.00881 0.0220 0.4737 0.0316
-4.000 -0.3527 0.01547 0.00828 0.0225 0.4645 0.0319
-3.750 -0.3255 0.01480 0.00752 0.0229 0.4557 0.0321
-3.500 -0.2979 0.01397 0.00668 0.0231 0.4473 0.0324
-3.250 -0.2709 0.01351 0.00620 0.0235 0.4387 0.0328
-3.000 -0.2437 0.01313 0.00582 0.0239 0.4316 0.0331
-2.750 -0.2167 0.01284 0.00551 0.0243 0.4242 0.0335
-2.500 -0.1896 0.01252 0.00519 0.0247 0.4184 0.0339
-2.250 -0.1627 0.01221 0.00486 0.0252 0.4124 0.0343
-2.000 -0.1359 0.01196 0.00457 0.0256 0.4055 0.0349
-1.750 -0.1087 0.01175 0.00435 0.0261 0.4008 0.0356
-1.500 -0.0810 0.01166 0.00423 0.0264 0.3959 0.0361
-1.250 -0.0559 0.01120 0.00377 0.0272 0.3906 0.0367
-1.000 -0.0299 0.01095 0.00352 0.0277 0.3852 0.0373
-0.750 -0.0031 0.01075 0.00335 0.0282 0.3814 0.0379
-0.500 0.0238 0.01058 0.00318 0.0286 0.3771 0.0386
-0.250 0.0507 0.01046 0.00304 0.0291 0.3726 0.0394
0.000 0.0778 0.01038 0.00294 0.0295 0.3676 0.0402
0.250 0.1052 0.01025 0.00282 0.0298 0.3645 0.0409
0.500 0.1315 0.01003 0.00262 0.0304 0.3607 0.0422
0.750 0.1587 0.00994 0.00253 0.0307 0.3569 0.0435
1.000 0.1859 0.00990 0.00246 0.0311 0.3525 0.0446
1.250 0.2136 0.00986 0.00243 0.0313 0.3492 0.0455
1.500 0.2406 0.00971 0.00230 0.0317 0.3465 0.0471
1.750 0.2682 0.00964 0.00224 0.0320 0.3430 0.0489
2.000 0.2958 0.00962 0.00221 0.0323 0.3393 0.0508
2.250 0.3230 0.00961 0.00218 0.0326 0.3351 0.0534
2.500 0.3508 0.00961 0.00217 0.0328 0.3321 0.0562
2.750 0.3781 0.00951 0.00216 0.0331 0.3297 0.0913
3.000 0.4026 0.00917 0.00218 0.0338 0.3269 0.2266
3.250 0.4115 0.00770 0.00209 0.0372 0.3244 0.6864
3.500 0.4286 0.00729 0.00218 0.0397 0.3215 0.8275
3.750 0.4525 0.00726 0.00233 0.0409 0.3175 0.8883
4.000 0.4799 0.00730 0.00245 0.0413 0.3148 0.9185
4.250 0.5097 0.00736 0.00257 0.0412 0.3122 0.9373
4.500 0.5400 0.00746 0.00269 0.0410 0.3090 0.9518
4.750 0.5763 0.00763 0.00284 0.0395 0.3045 0.9603
5.000 0.6045 0.00783 0.00301 0.0395 0.2995 0.9681
5.250 0.6445 0.00795 0.00315 0.0372 0.2971 0.9709
5.500 0.6862 0.00810 0.00330 0.0344 0.2931 0.9734
5.750 0.7236 0.00827 0.00344 0.0325 0.2883 0.9762
6.000 0.7544 0.00849 0.00361 0.0319 0.2834 0.9797
6.250 0.7909 0.00858 0.00374 0.0302 0.2806 0.9822
6.500 0.8292 0.00869 0.00385 0.0281 0.2768 0.9833
6.750 0.8639 0.00883 0.00397 0.0266 0.2726 0.9845
7.000 0.8975 0.00902 0.00413 0.0253 0.2675 0.9858
7.250 0.9312 0.00910 0.00424 0.0240 0.2648 0.9873
7.500 0.9641 0.00921 0.00437 0.0229 0.2608 0.9891
7.750 0.9957 0.00938 0.00452 0.0220 0.2561 0.9910
8.000 1.0256 0.00959 0.00472 0.0214 0.2515 0.9931
8.250 1.0601 0.00967 0.00483 0.0199 0.2474 0.9939
8.500 1.0938 0.00983 0.00498 0.0185 0.2419 0.9950
8.750 1.1269 0.01002 0.00516 0.0172 0.2352 0.9964
9.000 1.1598 0.01019 0.00533 0.0159 0.2282 0.9977
9.250 1.1920 0.01044 0.00555 0.0147 0.2212 0.9990
9.500 1.2246 0.01062 0.00575 0.0134 0.2147 1.0000
9.750 1.2452 0.01094 0.00603 0.0145 0.2073 1.0000
10.000 1.2668 0.01115 0.00626 0.0154 0.2009 1.0000
10.250 1.2866 0.01151 0.00660 0.0166 0.1925 1.0000
10.500 1.3066 0.01185 0.00692 0.0177 0.1829 1.0000
10.750 1.3252 0.01229 0.00732 0.0190 0.1714 1.0000
11.000 1.3419 0.01286 0.00783 0.0205 0.1572 1.0000
11.250 1.3576 0.01349 0.00839 0.0220 0.1445 1.0000
11.500 1.3730 0.01412 0.00898 0.0236 0.1345 1.0000
11.750 1.3875 0.01479 0.00962 0.0252 0.1262 1.0000
12.000 1.4029 0.01538 0.01021 0.0267 0.1201 1.0000
12.250 1.4166 0.01607 0.01089 0.0284 0.1144 1.0000
12.500 1.4317 0.01665 0.01150 0.0298 0.1103 1.0000
12.750 1.4429 0.01745 0.01230 0.0315 0.1057 1.0000
13.000 1.4551 0.01818 0.01307 0.0331 0.1021 1.0000
13.250 1.4647 0.01904 0.01396 0.0347 0.0984 1.0000
13.500 1.4622 0.02032 0.01528 0.0375 0.0954 1.0000
13.750 1.4561 0.02342 0.01847 0.0362 0.0927 1.0000
14.000 1.4584 0.02581 0.02094 0.0355 0.0899 1.0000
14.250 1.4547 0.02860 0.02377 0.0351 0.0870 1.0000
14.500 1.4451 0.03190 0.02711 0.0346 0.0839 1.0000
14.750 1.4411 0.03468 0.02995 0.0343 0.0816 1.0000
15.000 1.4344 0.03777 0.03309 0.0338 0.0789 1.0000
15.250 1.4232 0.04139 0.03675 0.0332 0.0762 1.0000
15.500 1.4113 0.04519 0.04061 0.0324 0.0734 1.0000
15.750 1.4038 0.04862 0.04411 0.0316 0.0715 1.0000
16.000 1.3922 0.05272 0.04826 0.0304 0.0686 1.0000
16.250 1.3791 0.05711 0.05269 0.0291 0.0663 1.0000
16.500 1.3715 0.06089 0.05653 0.0279 0.0640 1.0000
16.750 1.3616 0.06505 0.06075 0.0266 0.0619 1.0000
17.000 1.3480 0.06971 0.06544 0.0250 0.0596 1.0000
17.250 1.3374 0.07407 0.06986 0.0235 0.0577 1.0000
17.500 1.3308 0.07793 0.07377 0.0222 0.0557 1.0000
17.750 1.3196 0.08250 0.07838 0.0206 0.0538 1.0000
18.000 1.3080 0.08718 0.08309 0.0188 0.0519 1.0000
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