MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MARSKE XM-1D AIRFOIL (F14-3.0) (marske1-il) Reynolds number: 50,000 Max Cl/Cd: 17.82 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-marske1-il-50000-n5.txt Download as CSV file: xf-marske1-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5005 0.10282 0.09660 0.0017 1.0000 0.0921
-9.750 -0.4834 0.09961 0.09344 0.0015 1.0000 0.0898
-9.500 -0.5064 0.09116 0.08492 -0.0067 0.8528 0.0840
-9.250 -0.5019 0.08709 0.08066 -0.0088 0.8133 0.0825
-9.000 -0.5125 0.08197 0.07538 -0.0116 0.7946 0.0806
-8.750 -0.5561 0.07470 0.06781 -0.0141 0.7863 0.0774
-8.500 -0.5568 0.07141 0.06436 -0.0137 0.7722 0.0766
-8.250 -0.5596 0.06781 0.06055 -0.0133 0.7604 0.0757
-7.750 -0.5629 0.06056 0.05272 -0.0116 0.7404 0.0744
-7.500 -0.5599 0.05736 0.04916 -0.0103 0.7313 0.0743
-7.250 -0.5529 0.05433 0.04579 -0.0091 0.7214 0.0744
-7.000 -0.5437 0.05158 0.04265 -0.0076 0.7126 0.0744
-6.750 -0.5311 0.04892 0.03962 -0.0064 0.7032 0.0743
-6.500 -0.5169 0.04644 0.03671 -0.0049 0.6944 0.0739
-6.250 -0.5000 0.04412 0.03399 -0.0037 0.6853 0.0735
-6.000 -0.4811 0.04208 0.03155 -0.0024 0.6762 0.0733
-5.750 -0.4597 0.04027 0.02939 -0.0014 0.6676 0.0732
-5.500 -0.4368 0.03869 0.02752 -0.0006 0.6583 0.0736
-5.250 -0.4131 0.03735 0.02593 0.0002 0.6497 0.0746
-5.000 -0.3878 0.03610 0.02443 0.0008 0.6402 0.0759
-4.750 -0.3616 0.03494 0.02298 0.0015 0.6322 0.0769
-4.500 -0.3333 0.03384 0.02168 0.0017 0.6227 0.0776
-4.250 -0.3051 0.03290 0.02064 0.0021 0.6149 0.0782
-4.000 -0.2750 0.03205 0.01979 0.0019 0.6052 0.0791
-3.750 -0.2458 0.03135 0.01896 0.0023 0.5982 0.0803
-3.500 -0.2151 0.03077 0.01836 0.0020 0.5882 0.0826
-3.250 -0.1862 0.03026 0.01772 0.0024 0.5814 0.0851
-3.000 -0.1574 0.02983 0.01731 0.0022 0.5720 0.0877
-2.750 -0.1309 0.02942 0.01678 0.0029 0.5653 0.0901
-2.500 -0.1045 0.02911 0.01644 0.0031 0.5572 0.0926
-2.250 -0.0794 0.02877 0.01606 0.0038 0.5499 0.0963
-2.000 -0.0549 0.02849 0.01571 0.0046 0.5437 0.1021
-1.750 -0.0305 0.02828 0.01554 0.0050 0.5356 0.1104
-1.500 -0.0079 0.02789 0.01518 0.0062 0.5302 0.1228
-1.250 0.0122 0.02743 0.01515 0.0071 0.5235 0.1610
-0.750 0.1019 0.02603 0.01638 0.0058 0.5105 0.8772
-0.500 0.1498 0.02683 0.01706 0.0028 0.5010 0.9133
-0.250 0.2125 0.02718 0.01712 -0.0023 0.4945 0.9497
0.000 0.2803 0.02754 0.01730 -0.0097 0.4857 0.9796
0.250 0.3420 0.02743 0.01698 -0.0163 0.4785 1.0000
0.500 0.3623 0.02746 0.01683 -0.0150 0.4748 1.0000
0.750 0.3839 0.02804 0.01742 -0.0150 0.4679 1.0000
1.000 0.4044 0.02838 0.01769 -0.0142 0.4623 1.0000
1.250 0.4245 0.02852 0.01770 -0.0130 0.4583 1.0000
1.500 0.4446 0.02878 0.01785 -0.0119 0.4543 1.0000
1.750 0.4645 0.02970 0.01884 -0.0119 0.4474 1.0000
2.000 0.4840 0.03012 0.01920 -0.0109 0.4426 1.0000
2.250 0.5037 0.03031 0.01927 -0.0095 0.4390 1.0000
2.500 0.5227 0.03088 0.01980 -0.0085 0.4345 1.0000
2.750 0.5398 0.03209 0.02111 -0.0083 0.4280 1.0000
3.000 0.5580 0.03271 0.02170 -0.0073 0.4236 1.0000
3.250 0.5771 0.03299 0.02190 -0.0058 0.4203 1.0000
3.500 0.5956 0.03347 0.02231 -0.0044 0.4168 1.0000
3.750 0.6066 0.03549 0.02451 -0.0044 0.4091 1.0000
4.000 0.6223 0.03637 0.02540 -0.0033 0.4048 1.0000
4.250 0.6402 0.03686 0.02583 -0.0018 0.4017 1.0000
4.500 0.6602 0.03705 0.02593 -0.0001 0.3992 1.0000
4.750 0.6565 0.04064 0.02976 -0.0002 0.3901 1.0000
5.000 0.6690 0.04173 0.03086 0.0011 0.3857 1.0000
5.250 0.6859 0.04228 0.03138 0.0027 0.3826 1.0000
5.500 0.7060 0.04254 0.03158 0.0044 0.3804 1.0000
5.750 0.6713 0.04895 0.03821 0.0040 0.3690 1.0000
6.000 0.6843 0.04985 0.03909 0.0055 0.3653 1.0000
6.250 0.7046 0.05002 0.03923 0.0073 0.3629 1.0000
6.750 0.6527 0.05995 0.04919 0.0075 0.3468 1.0000
7.000 0.6746 0.06015 0.04938 0.0091 0.3443 1.0000
7.500 0.6305 0.06852 0.05769 0.0100 0.3299 1.0000
7.750 0.6510 0.06898 0.05815 0.0113 0.3266 1.0000
8.250 0.6338 0.07567 0.06483 0.0112 0.3127 1.0000
8.500 0.6564 0.07593 0.06510 0.0125 0.3090 1.0000
8.750 0.6410 0.08016 0.06933 0.0117 0.3008 1.0000
9.000 0.6490 0.08194 0.07113 0.0121 0.2947 1.0000
9.250 0.6735 0.08197 0.07117 0.0134 0.2912 1.0000
9.500 0.6528 0.08706 0.07628 0.0119 0.2818 1.0000
9.750 0.6676 0.08819 0.07743 0.0126 0.2767 1.0000
10.000 0.6941 0.08793 0.07721 0.0140 0.2736 1.0000
10.250 0.6675 0.09407 0.08338 0.0118 0.2632 1.0000
10.500 0.6875 0.09460 0.08393 0.0127 0.2590 1.0000
10.750 0.6755 0.09919 0.08855 0.0112 0.2508 1.0000
11.000 0.6844 0.10121 0.09060 0.0113 0.2452 1.0000
11.250 0.7071 0.10140 0.09084 0.0124 0.2419 1.0000
11.500 0.6855 0.10754 0.09701 0.0099 0.2323 1.0000
11.750 0.7017 0.10860 0.09811 0.0104 0.2280 1.0000
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Polar data table (+)
Polar graphs
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