MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 100,000 Max Cl/Cd: 38.39 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske1-il-100000-n5.txt Download as CSV file: xf-marske1-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5004 0.09789 0.09239 0.0030 0.6652 0.1124
-9.250 -0.4789 0.09552 0.08998 0.0049 0.6574 0.1142
-8.750 -0.6230 0.06446 0.05821 -0.0098 0.6647 0.0561
-8.500 -0.6148 0.06174 0.05539 -0.0089 0.6583 0.0549
-8.250 -0.6156 0.05826 0.05167 -0.0076 0.6535 0.0543
-8.000 -0.6151 0.05470 0.04783 -0.0061 0.6480 0.0540
-7.750 -0.6114 0.05135 0.04417 -0.0045 0.6423 0.0537
-7.500 -0.6054 0.04820 0.04063 -0.0026 0.6371 0.0532
-7.000 -0.5893 0.04213 0.03338 0.0021 0.6261 0.0510
-6.750 -0.5718 0.04013 0.03110 0.0034 0.6198 0.0508
-6.500 -0.5533 0.03828 0.02893 0.0048 0.6138 0.0507
-6.250 -0.5333 0.03654 0.02692 0.0060 0.6067 0.0506
-6.000 -0.5128 0.03502 0.02502 0.0073 0.6006 0.0507
-5.750 -0.4914 0.03366 0.02330 0.0085 0.5939 0.0513
-5.500 -0.4667 0.03220 0.02179 0.0090 0.5866 0.0521
-5.250 -0.4424 0.03100 0.02038 0.0098 0.5810 0.0527
-5.000 -0.4168 0.02984 0.01906 0.0104 0.5730 0.0530
-4.750 -0.3909 0.02878 0.01781 0.0111 0.5662 0.0532
-4.500 -0.3643 0.02781 0.01669 0.0116 0.5593 0.0534
-4.250 -0.3372 0.02691 0.01568 0.0121 0.5518 0.0537
-4.000 -0.3103 0.02609 0.01471 0.0126 0.5463 0.0541
-3.750 -0.2827 0.02535 0.01391 0.0129 0.5381 0.0548
-3.500 -0.2559 0.02476 0.01315 0.0135 0.5314 0.0558
-3.250 -0.2285 0.02382 0.01234 0.0138 0.5247 0.0570
-3.000 -0.2019 0.02312 0.01170 0.0142 0.5172 0.0579
-2.750 -0.1762 0.02252 0.01106 0.0149 0.5117 0.0586
-2.500 -0.1505 0.02202 0.01059 0.0155 0.5048 0.0593
-2.250 -0.1254 0.02157 0.01011 0.0163 0.4982 0.0600
-2.000 -0.1006 0.02115 0.00960 0.0172 0.4931 0.0608
-1.750 -0.0764 0.02068 0.00920 0.0180 0.4859 0.0625
-1.500 -0.0514 0.02033 0.00881 0.0187 0.4798 0.0646
-1.250 -0.0262 0.02002 0.00842 0.0196 0.4751 0.0663
-1.000 -0.0007 0.01979 0.00821 0.0202 0.4689 0.0681
-0.750 0.0251 0.01961 0.00800 0.0208 0.4628 0.0702
-0.500 0.0507 0.01939 0.00775 0.0216 0.4578 0.0735
0.000 0.0982 0.01856 0.00763 0.0231 0.4469 0.2240
0.500 0.1493 0.01665 0.00779 0.0251 0.4377 0.7796
0.750 0.1897 0.01695 0.00821 0.0237 0.4314 0.8502
1.000 0.2265 0.01728 0.00851 0.0228 0.4255 0.8875
1.250 0.2662 0.01760 0.00871 0.0214 0.4208 0.9121
1.500 0.3138 0.01801 0.00900 0.0183 0.4156 0.9341
1.750 0.3610 0.01839 0.00935 0.0150 0.4091 0.9511
2.000 0.4100 0.01864 0.00948 0.0112 0.4037 0.9661
2.250 0.4586 0.01880 0.00948 0.0074 0.3995 0.9782
2.500 0.5149 0.01901 0.00971 0.0016 0.3934 0.9922
2.750 0.5585 0.01909 0.00976 -0.0017 0.3878 0.9997
3.000 0.5815 0.01922 0.00982 -0.0010 0.3841 1.0000
3.250 0.6034 0.01936 0.00985 0.0000 0.3809 1.0000
3.500 0.6251 0.01964 0.01017 0.0008 0.3773 1.0000
3.750 0.6466 0.01996 0.01055 0.0016 0.3730 1.0000
4.000 0.6680 0.02022 0.01082 0.0025 0.3690 1.0000
4.250 0.6896 0.02044 0.01100 0.0035 0.3655 1.0000
4.500 0.7113 0.02063 0.01111 0.0046 0.3624 1.0000
4.750 0.7324 0.02102 0.01154 0.0055 0.3589 1.0000
5.000 0.7528 0.02149 0.01212 0.0064 0.3548 1.0000
5.250 0.7734 0.02189 0.01258 0.0074 0.3512 1.0000
5.500 0.7945 0.02221 0.01289 0.0084 0.3478 1.0000
5.750 0.8160 0.02245 0.01309 0.0095 0.3448 1.0000
6.000 0.8370 0.02282 0.01344 0.0106 0.3417 1.0000
6.250 0.8553 0.02351 0.01431 0.0116 0.3374 1.0000
6.500 0.8745 0.02407 0.01497 0.0126 0.3337 1.0000
6.750 0.8947 0.02447 0.01540 0.0137 0.3302 1.0000
7.000 0.9163 0.02470 0.01559 0.0148 0.3270 1.0000
7.250 0.9365 0.02506 0.01596 0.0159 0.3231 1.0000
7.500 0.9522 0.02577 0.01686 0.0171 0.3169 1.0000
7.750 0.9725 0.02596 0.01706 0.0183 0.3118 1.0000
8.000 0.9955 0.02593 0.01694 0.0194 0.3079 1.0000
8.250 1.0100 0.02678 0.01797 0.0206 0.3027 1.0000
8.500 1.0260 0.02746 0.01879 0.0219 0.2978 1.0000
8.750 1.0456 0.02778 0.01913 0.0230 0.2938 1.0000
9.000 1.0682 0.02787 0.01916 0.0240 0.2905 1.0000
9.250 1.0778 0.02903 0.02055 0.0254 0.2852 1.0000
9.500 1.0909 0.02981 0.02146 0.0268 0.2801 1.0000
9.750 1.1102 0.03003 0.02168 0.0279 0.2759 1.0000
10.000 1.1259 0.03056 0.02225 0.0292 0.2716 1.0000
10.250 1.1274 0.03206 0.02397 0.0310 0.2658 1.0000
10.500 1.1399 0.03266 0.02462 0.0324 0.2609 1.0000
10.750 1.1583 0.03281 0.02473 0.0336 0.2565 1.0000
11.000 1.1364 0.03557 0.02773 0.0361 0.2509 1.0000
11.250 1.1235 0.03796 0.03019 0.0371 0.2458 1.0000
11.500 1.1485 0.03749 0.02963 0.0383 0.2413 1.0000
11.750 1.0674 0.04778 0.04020 0.0350 0.2334 1.0000
12.000 1.0837 0.04815 0.04056 0.0357 0.2282 1.0000
12.250 1.0026 0.06044 0.05298 0.0309 0.2174 1.0000
12.500 1.0310 0.05925 0.05178 0.0322 0.2133 1.0000
12.750 0.9717 0.06993 0.06254 0.0280 0.2019 1.0000
13.000 0.9999 0.06865 0.06125 0.0292 0.1983 1.0000
13.500 0.9803 0.07706 0.06972 0.0265 0.1841 1.0000
13.750 1.0190 0.07414 0.06677 0.0285 0.1815 1.0000
14.000 0.9651 0.08544 0.07818 0.0237 0.1708 1.0000
14.250 0.9986 0.08317 0.07589 0.0253 0.1682 1.0000
14.500 0.9518 0.09395 0.08675 0.0207 0.1587 1.0000
14.750 0.9787 0.09266 0.08546 0.0217 0.1559 1.0000
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Polar data table (+)
Polar graphs
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