MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 50,000 Max Cl/Cd: 9.4 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-marske1-il-50000.txt Download as CSV file: xf-marske1-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4673 0.12595 0.11999 0.0261 1.0000 0.2703
-10.000 -0.4324 0.12056 0.11464 0.0266 1.0000 0.2813
-9.750 -0.4461 0.11851 0.11273 0.0242 1.0000 0.2906
-9.500 -0.4165 0.11386 0.10813 0.0240 1.0000 0.3023
-9.250 -0.4160 0.11062 0.10502 0.0222 1.0000 0.3125
-9.000 -0.4242 0.10913 0.10365 0.0205 1.0000 0.3277
-8.750 -0.3851 0.10332 0.09790 0.0197 1.0000 0.3376
-8.500 -0.3845 0.10040 0.09511 0.0179 1.0000 0.3522
-8.250 -0.3888 0.09821 0.09307 0.0161 1.0000 0.3696
-8.000 -0.3870 0.09591 0.09092 0.0147 1.0000 0.3884
-7.750 -0.3643 0.09207 0.08717 0.0132 1.0000 0.4085
-7.500 -0.3182 0.08714 0.08224 0.0108 0.9357 0.4313
-7.250 -0.2773 0.08319 0.07809 0.0073 0.8923 0.4575
-7.000 -0.2671 0.08114 0.07594 0.0079 0.8679 0.4879
-6.750 -0.2411 0.07846 0.07312 0.0084 0.8459 0.5109
-6.250 -0.4280 0.05610 0.04933 -0.0257 0.8500 0.1936
-6.000 -0.4073 0.05263 0.04590 -0.0253 0.8346 0.1869
-5.750 -0.3996 0.04925 0.04189 -0.0240 0.8227 0.1730
-5.500 -0.3897 0.04609 0.03797 -0.0225 0.8103 0.1616
-5.250 -0.3701 0.04405 0.03568 -0.0215 0.7976 0.1580
-5.000 -0.3515 0.04215 0.03347 -0.0200 0.7860 0.1548
-4.750 -0.3303 0.04032 0.03128 -0.0192 0.7734 0.1517
-4.500 -0.3084 0.03889 0.02949 -0.0182 0.7623 0.1506
-4.250 -0.2845 0.03774 0.02806 -0.0173 0.7513 0.1513
-4.000 -0.2583 0.03674 0.02683 -0.0171 0.7400 0.1523
-3.750 -0.2323 0.03587 0.02569 -0.0160 0.7303 0.1531
-3.500 -0.2016 0.03511 0.02478 -0.0167 0.7190 0.1541
-3.250 -0.1698 0.03452 0.02401 -0.0165 0.7100 0.1563
-3.000 -0.1341 0.03415 0.02351 -0.0179 0.6989 0.1605
-2.750 -0.0991 0.03378 0.02327 -0.0187 0.6897 0.1682
-2.500 -0.0671 0.03373 0.02317 -0.0196 0.6801 0.1770
-2.250 -0.0421 0.03362 0.02317 -0.0187 0.6727 0.1878
-2.000 -0.0194 0.03373 0.02345 -0.0189 0.6637 0.2040
-1.750 0.2298 0.03287 0.02483 -0.0452 0.6414 1.0000
-1.500 0.2504 0.03363 0.02542 -0.0452 0.6342 1.0000
-1.250 0.2720 0.03445 0.02611 -0.0458 0.6262 1.0000
-1.000 0.2893 0.03514 0.02661 -0.0443 0.6205 1.0000
-0.750 0.3118 0.03639 0.02782 -0.0462 0.6132 1.0000
-0.500 0.3303 0.03734 0.02866 -0.0460 0.6066 1.0000
-0.250 0.3469 0.03828 0.02946 -0.0449 0.6010 1.0000
0.000 0.3649 0.03995 0.03113 -0.0468 0.5946 1.0000
0.250 0.3804 0.04121 0.03232 -0.0465 0.5893 1.0000
0.500 0.3956 0.04208 0.03304 -0.0442 0.5845 1.0000
0.750 0.4045 0.04443 0.03544 -0.0463 0.5792 1.0000
1.000 0.4112 0.04646 0.03746 -0.0465 0.5757 1.0000
1.250 0.4160 0.04843 0.03939 -0.0460 0.5730 1.0000
1.500 0.4221 0.05017 0.04107 -0.0448 0.5701 1.0000
1.750 0.4355 0.05150 0.04230 -0.0428 0.5659 1.0000
2.000 0.4193 0.05448 0.04530 -0.0422 0.5684 1.0000
3.000 0.2194 0.06588 0.05665 -0.0289 0.7301 1.0000
3.250 0.2221 0.06659 0.05725 -0.0261 0.7134 1.0000
3.500 0.2247 0.06759 0.05814 -0.0237 0.6987 1.0000
3.750 0.2372 0.06944 0.05989 -0.0226 0.6872 1.0000
4.250 0.2617 0.07271 0.06299 -0.0204 0.6615 1.0000
4.500 0.2904 0.07605 0.06624 -0.0214 0.6550 1.0000
4.750 0.2859 0.07641 0.06654 -0.0186 0.6419 1.0000
5.000 0.2952 0.07841 0.06847 -0.0177 0.6338 1.0000
5.250 0.3132 0.08050 0.07050 -0.0173 0.6224 1.0000
5.500 0.3123 0.08176 0.07170 -0.0155 0.6132 1.0000
5.750 0.3352 0.08448 0.07438 -0.0157 0.6044 1.0000
6.000 0.3322 0.08565 0.07550 -0.0140 0.5955 1.0000
6.250 0.3583 0.08869 0.07852 -0.0145 0.5862 1.0000
6.500 0.3519 0.08962 0.07940 -0.0127 0.5770 1.0000
6.750 0.3771 0.09275 0.08251 -0.0131 0.5684 1.0000
7.000 0.3717 0.09383 0.08356 -0.0116 0.5593 1.0000
7.250 0.3991 0.09726 0.08699 -0.0122 0.5498 1.0000
7.500 0.3912 0.09816 0.08786 -0.0107 0.5405 1.0000
7.750 0.4205 0.10194 0.09164 -0.0114 0.5312 1.0000
8.000 0.4106 0.10263 0.09231 -0.0100 0.5210 1.0000
8.250 0.4435 0.10706 0.09676 -0.0109 0.5125 1.0000
8.500 0.4298 0.10732 0.09701 -0.0095 0.5015 1.0000
9.000 0.4487 0.11223 0.10193 -0.0092 0.4825 1.0000
9.250 0.4827 0.11763 0.10736 -0.0101 0.4754 1.0000
9.500 0.4685 0.11739 0.10711 -0.0090 0.4630 1.0000
9.750 0.4969 0.12259 0.11235 -0.0098 0.4574 1.0000
10.000 0.4835 0.12252 0.11228 -0.0090 0.4458 1.0000
10.250 0.5133 0.12793 0.11772 -0.0098 0.4394 1.0000
10.500 0.4989 0.12779 0.11758 -0.0092 0.4283 1.0000
10.750 0.5358 0.13399 0.12384 -0.0100 0.4222 1.0000
11.000 0.5121 0.13322 0.12304 -0.0097 0.4134 1.0000
11.250 0.5395 0.13778 0.12766 -0.0101 0.4052 1.0000
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Polar data table (+)
Polar graphs
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