MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 500,000 Max Cl/Cd: 89.77 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske1-il-500000.txt Download as CSV file: xf-marske1-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4870 0.09871 0.09541 0.0083 0.6138 0.0363
-10.750 -0.4788 0.09605 0.09275 0.0083 0.6100 0.0365
-10.500 -0.5871 0.07818 0.07463 -0.0118 0.6212 0.0365
-10.250 -0.5954 0.07393 0.07035 -0.0139 0.6186 0.0366
-10.000 -0.6087 0.06977 0.06616 -0.0153 0.6162 0.0367
-9.750 -0.6242 0.06613 0.06246 -0.0152 0.6136 0.0368
-9.500 -0.6394 0.06303 0.05929 -0.0136 0.6107 0.0369
-9.250 -0.6521 0.06051 0.05669 -0.0109 0.6078 0.0370
-9.000 -0.6551 0.05818 0.05427 -0.0090 0.6046 0.0372
-8.750 -0.6571 0.05550 0.05147 -0.0073 0.6015 0.0375
-8.500 -0.6572 0.05262 0.04848 -0.0055 0.5986 0.0378
-8.250 -0.6556 0.04968 0.04539 -0.0036 0.5951 0.0384
-8.000 -0.6944 0.04637 0.04081 0.0046 0.5939 0.0407
-7.750 -0.6788 0.04154 0.03597 0.0051 0.5900 0.0411
-7.500 -0.6570 0.03900 0.03348 0.0053 0.5857 0.0414
-7.250 -0.6378 0.03708 0.03155 0.0061 0.5812 0.0417
-7.000 -0.6190 0.03537 0.02978 0.0071 0.5763 0.0422
-6.750 -0.6007 0.03373 0.02802 0.0084 0.5717 0.0429
-6.500 -0.5915 0.03429 0.02775 0.0125 0.5678 0.0455
-6.250 -0.5723 0.03054 0.02393 0.0132 0.5634 0.0462
-6.000 -0.5476 0.02854 0.02202 0.0134 0.5577 0.0468
-5.750 -0.5245 0.02714 0.02055 0.0142 0.5523 0.0476
-5.500 -0.5017 0.02601 0.01926 0.0152 0.5468 0.0489
-5.250 -0.4827 0.02511 0.01790 0.0173 0.5406 0.0516
-5.000 -0.4565 0.02339 0.01623 0.0175 0.5342 0.0525
-4.750 -0.4310 0.02235 0.01512 0.0180 0.5281 0.0539
-4.500 -0.4077 0.02137 0.01391 0.0191 0.5207 0.0578
-4.250 -0.3809 0.02026 0.01280 0.0194 0.5136 0.0595
-4.000 -0.3559 0.01934 0.01173 0.0201 0.5057 0.0644
-3.750 -0.3287 0.01851 0.01089 0.0204 0.4972 0.0666
-3.500 -0.3031 0.01804 0.01018 0.0213 0.4894 0.0702
-3.250 -0.2976 0.02100 0.01368 0.0270 0.4860 0.0559
-3.000 -0.2404 0.01668 0.00832 0.0227 0.4735 0.0463
-2.750 -0.2136 0.01677 0.00825 0.0235 0.4654 0.0458
-2.500 -0.1844 0.01591 0.00740 0.0235 0.4577 0.0454
-2.250 -0.1563 0.01543 0.00692 0.0238 0.4503 0.0455
-2.000 -0.1286 0.01472 0.00620 0.0241 0.4435 0.0461
-1.750 -0.1015 0.01412 0.00565 0.0244 0.4375 0.0467
-1.500 -0.0748 0.01368 0.00525 0.0249 0.4312 0.0471
-1.250 -0.0486 0.01334 0.00490 0.0255 0.4252 0.0475
-1.000 -0.0226 0.01306 0.00462 0.0261 0.4196 0.0481
-0.750 0.0037 0.01278 0.00437 0.0267 0.4145 0.0487
-0.500 0.0298 0.01258 0.00414 0.0273 0.4093 0.0495
-0.250 0.0562 0.01250 0.00400 0.0278 0.4038 0.0505
0.000 0.0818 0.01219 0.00374 0.0285 0.3997 0.0517
0.250 0.1075 0.01192 0.00351 0.0291 0.3952 0.0529
0.500 0.1338 0.01178 0.00336 0.0297 0.3909 0.0541
0.750 0.1601 0.01175 0.00328 0.0302 0.3861 0.0555
1.000 0.1873 0.01164 0.00319 0.0305 0.3825 0.0568
1.250 0.2140 0.01151 0.00306 0.0310 0.3783 0.0597
1.500 0.2412 0.01147 0.00299 0.0314 0.3743 0.0629
1.750 0.2673 0.01140 0.00299 0.0319 0.3704 0.0925
2.000 0.2912 0.01110 0.00303 0.0327 0.3669 0.2135
2.250 0.3059 0.00995 0.00293 0.0349 0.3641 0.5372
2.500 0.3158 0.00904 0.00302 0.0389 0.3612 0.8005
2.750 0.3418 0.00896 0.00320 0.0399 0.3574 0.8757
3.000 0.3732 0.00911 0.00339 0.0396 0.3534 0.9139
3.250 0.4067 0.00936 0.00363 0.0389 0.3495 0.9377
3.500 0.4407 0.00954 0.00384 0.0381 0.3463 0.9524
3.750 0.4891 0.00980 0.00409 0.0342 0.3422 0.9592
4.000 0.5247 0.01004 0.00430 0.0330 0.3386 0.9677
4.250 0.5754 0.01039 0.00456 0.0285 0.3339 0.9706
4.500 0.6244 0.01059 0.00478 0.0244 0.3301 0.9754
4.750 0.6616 0.01076 0.00496 0.0226 0.3264 0.9815
5.000 0.7061 0.01085 0.00503 0.0193 0.3221 0.9838
5.250 0.7442 0.01103 0.00514 0.0171 0.3173 0.9864
5.500 0.7805 0.01111 0.00526 0.0154 0.3135 0.9893
5.750 0.8135 0.01117 0.00535 0.0142 0.3093 0.9920
6.000 0.8479 0.01124 0.00541 0.0128 0.3051 0.9940
6.250 0.8826 0.01141 0.00551 0.0112 0.3003 0.9960
6.500 0.9178 0.01145 0.00561 0.0096 0.2965 0.9981
6.750 0.9528 0.01151 0.00572 0.0080 0.2927 1.0000
7.000 0.9756 0.01162 0.00583 0.0088 0.2892 1.0000
7.250 0.9979 0.01178 0.00597 0.0098 0.2856 1.0000
7.500 1.0201 0.01196 0.00617 0.0107 0.2820 1.0000
7.750 1.0428 0.01206 0.00634 0.0115 0.2785 1.0000
8.000 1.0652 0.01219 0.00650 0.0124 0.2746 1.0000
8.250 1.0871 0.01237 0.00667 0.0134 0.2706 1.0000
8.500 1.1085 0.01261 0.00691 0.0144 0.2667 1.0000
8.750 1.1309 0.01273 0.00712 0.0153 0.2626 1.0000
9.000 1.1527 0.01289 0.00731 0.0162 0.2577 1.0000
9.250 1.1732 0.01317 0.00755 0.0173 0.2525 1.0000
9.500 1.1954 0.01332 0.00779 0.0182 0.2471 1.0000
9.750 1.2164 0.01355 0.00802 0.0192 0.2407 1.0000
10.000 1.2369 0.01383 0.00832 0.0203 0.2347 1.0000
10.250 1.2578 0.01409 0.00862 0.0213 0.2282 1.0000
10.500 1.2768 0.01448 0.00899 0.0225 0.2215 1.0000
10.750 1.2973 0.01477 0.00934 0.0235 0.2143 1.0000
11.000 1.3153 0.01523 0.00979 0.0247 0.2062 1.0000
11.250 1.3339 0.01566 0.01025 0.0259 0.1971 1.0000
11.500 1.3507 0.01620 0.01079 0.0271 0.1873 1.0000
11.750 1.3652 0.01688 0.01145 0.0286 0.1763 1.0000
12.000 1.3771 0.01772 0.01226 0.0302 0.1644 1.0000
12.250 1.3863 0.01870 0.01320 0.0320 0.1534 1.0000
12.500 1.3938 0.01973 0.01424 0.0338 0.1447 1.0000
12.750 1.3931 0.02114 0.01566 0.0361 0.1381 1.0000
13.000 1.3841 0.02339 0.01799 0.0374 0.1335 1.0000
13.250 1.3743 0.02680 0.02144 0.0366 0.1289 1.0000
13.500 1.3690 0.02959 0.02428 0.0364 0.1249 1.0000
13.750 1.3628 0.03245 0.02719 0.0362 0.1210 1.0000
14.000 1.3515 0.03584 0.03061 0.0359 0.1177 1.0000
14.250 1.3414 0.03918 0.03399 0.0355 0.1144 1.0000
14.500 1.3377 0.04200 0.03688 0.0351 0.1113 1.0000
14.750 1.3287 0.04542 0.04035 0.0345 0.1081 1.0000
15.000 1.3159 0.04932 0.04428 0.0336 0.1053 1.0000
15.250 1.3102 0.05267 0.04769 0.0328 0.1023 1.0000
15.500 1.3068 0.05588 0.05097 0.0319 0.0992 1.0000
15.750 1.2984 0.05972 0.05485 0.0307 0.0960 1.0000
16.000 1.2873 0.06392 0.05905 0.0294 0.0930 1.0000
16.250 1.2861 0.06705 0.06228 0.0284 0.0901 1.0000
16.500 1.2795 0.07088 0.06614 0.0272 0.0868 1.0000
16.750 1.2700 0.07508 0.07035 0.0257 0.0839 1.0000
17.000 1.2658 0.07869 0.07403 0.0245 0.0810 1.0000
17.250 1.2611 0.08241 0.07779 0.0232 0.0778 1.0000
17.500 1.2511 0.08687 0.08225 0.0215 0.0750 1.0000
17.750 1.2475 0.09047 0.08591 0.0202 0.0724 1.0000
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