TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.67 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi8-il-1000000-n5.txt Download as CSV file: xf-tsagi8-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 8% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5842 0.08361 0.08208 -0.0096 1.0000 0.0026
-9.000 -0.5892 0.07873 0.07721 -0.0130 1.0000 0.0026
-8.750 -0.6048 0.07255 0.07106 -0.0187 1.0000 0.0026
-7.750 -0.7430 0.02224 0.01881 -0.0098 1.0000 0.0022
-7.500 -0.7313 0.01980 0.01602 -0.0071 1.0000 0.0023
-7.250 -0.7170 0.01792 0.01382 -0.0047 1.0000 0.0024
-7.000 -0.6976 0.01630 0.01192 -0.0033 0.9992 0.0026
-6.500 -0.6413 0.01397 0.00917 -0.0040 0.9900 0.0030
-6.250 -0.6116 0.01317 0.00819 -0.0046 0.9848 0.0031
-6.000 -0.5816 0.01208 0.00692 -0.0053 0.9786 0.0033
-5.750 -0.5495 0.01133 0.00608 -0.0065 0.9709 0.0036
-5.500 -0.5147 0.01073 0.00539 -0.0082 0.9602 0.0038
-5.250 -0.4782 0.01041 0.00503 -0.0103 0.9434 0.0044
-5.000 -0.4472 0.00999 0.00447 -0.0110 0.9167 0.0049
-4.750 -0.4219 0.00968 0.00398 -0.0104 0.8870 0.0051
-4.500 -0.3986 0.00928 0.00342 -0.0094 0.8600 0.0058
-4.250 -0.3746 0.00903 0.00306 -0.0085 0.8368 0.0066
-4.000 -0.3501 0.00886 0.00277 -0.0078 0.8150 0.0075
-3.750 -0.3251 0.00870 0.00251 -0.0071 0.7956 0.0086
-3.500 -0.3004 0.00847 0.00220 -0.0064 0.7771 0.0122
-3.250 -0.2752 0.00831 0.00199 -0.0059 0.7600 0.0178
-2.750 -0.2242 0.00806 0.00165 -0.0049 0.7279 0.0325
-2.500 -0.1985 0.00795 0.00149 -0.0045 0.7126 0.0405
-2.250 -0.1730 0.00779 0.00135 -0.0040 0.6985 0.0603
-2.000 -0.1479 0.00760 0.00123 -0.0035 0.6852 0.0922
-1.750 -0.1221 0.00749 0.00112 -0.0031 0.6719 0.1135
-1.250 -0.0713 0.00716 0.00094 -0.0023 0.6463 0.1901
-1.000 -0.0463 0.00697 0.00086 -0.0018 0.6342 0.2440
-0.750 -0.0216 0.00675 0.00079 -0.0012 0.6223 0.3060
-0.500 -0.0001 0.00626 0.00071 -0.0001 0.6111 0.4449
-0.250 0.0170 0.00558 0.00063 0.0019 0.6006 0.6353
0.000 0.0347 0.00513 0.00059 0.0041 0.5896 0.7608
0.250 0.0565 0.00492 0.00059 0.0056 0.5785 0.8340
0.500 0.0865 0.00480 0.00068 0.0053 0.5665 0.9092
0.750 0.1356 0.00494 0.00083 0.0006 0.5519 0.9455
1.000 0.1696 0.00507 0.00091 -0.0007 0.5386 0.9560
1.250 0.2018 0.00521 0.00101 -0.0017 0.5247 0.9644
1.500 0.2368 0.00537 0.00111 -0.0033 0.5089 0.9686
1.750 0.2697 0.00551 0.00118 -0.0045 0.4896 0.9707
2.000 0.2999 0.00563 0.00124 -0.0051 0.4706 0.9730
2.250 0.3266 0.00575 0.00131 -0.0049 0.4524 0.9761
2.500 0.3555 0.00590 0.00138 -0.0052 0.4296 0.9778
2.750 0.3868 0.00610 0.00147 -0.0062 0.3962 0.9788
3.000 0.4182 0.00626 0.00157 -0.0071 0.3748 0.9801
3.250 0.4487 0.00644 0.00168 -0.0079 0.3476 0.9816
3.500 0.4743 0.00710 0.00189 -0.0080 0.2413 0.9838
3.750 0.4971 0.00773 0.00219 -0.0073 0.1559 0.9867
4.000 0.5253 0.00838 0.00250 -0.0080 0.0751 0.9876
4.250 0.5541 0.00887 0.00279 -0.0086 0.0306 0.9886
4.500 0.5835 0.00919 0.00305 -0.0092 0.0146 0.9896
4.750 0.6129 0.00942 0.00331 -0.0097 0.0106 0.9908
5.000 0.6413 0.00976 0.00366 -0.0100 0.0074 0.9921
5.250 0.6694 0.01002 0.00396 -0.0103 0.0066 0.9933
5.500 0.6971 0.01033 0.00431 -0.0105 0.0059 0.9946
5.750 0.7253 0.01075 0.00476 -0.0109 0.0050 0.9955
6.000 0.7537 0.01121 0.00531 -0.0113 0.0045 0.9964
6.250 0.7821 0.01156 0.00571 -0.0117 0.0040 0.9973
6.500 0.8104 0.01197 0.00616 -0.0122 0.0035 0.9983
6.750 0.8384 0.01242 0.00666 -0.0126 0.0033 0.9992
7.000 0.8647 0.01314 0.00745 -0.0128 0.0029 1.0000
7.250 0.8820 0.01397 0.00838 -0.0109 0.0028 1.0000
7.500 0.9014 0.01451 0.00900 -0.0095 0.0027 1.0000
7.750 0.9196 0.01520 0.00980 -0.0079 0.0026 1.0000
8.000 0.9364 0.01604 0.01079 -0.0060 0.0024 1.0000
8.250 0.9528 0.01694 0.01182 -0.0041 0.0023 1.0000
8.500 0.9676 0.01807 0.01309 -0.0020 0.0022 1.0000
8.750 0.9821 0.01924 0.01442 0.0002 0.0021 1.0000
9.000 0.9974 0.02026 0.01557 0.0021 0.0020 1.0000
9.250 1.0140 0.02100 0.01641 0.0037 0.0019 1.0000
9.500 1.0255 0.02248 0.01808 0.0061 0.0019 1.0000
9.750 1.0399 0.02340 0.01912 0.0079 0.0018 1.0000
10.000 1.0551 0.02408 0.01987 0.0095 0.0017 1.0000
10.250 1.0647 0.02548 0.02144 0.0119 0.0017 1.0000
10.500 1.0674 0.02762 0.02383 0.0150 0.0016 1.0000
10.750 1.0540 0.03137 0.02799 0.0198 0.0015 1.0000
11.000 1.0386 0.03418 0.03108 0.0249 0.0015 1.0000
11.500 1.0067 0.04037 0.03771 0.0309 0.0015 1.0000
12.000 0.9758 0.04891 0.04664 0.0300 0.0016 1.0000
12.250 0.9473 0.05639 0.05435 0.0261 0.0015 1.0000
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Polar data table (+)
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