TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.8 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi8-il-1000000.txt Download as CSV file: xf-tsagi8-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5855 0.08371 0.08216 -0.0104 1.0000 0.0089
-9.000 -0.5887 0.07929 0.07776 -0.0136 1.0000 0.0091
-8.750 -0.6050 0.07222 0.07071 -0.0203 1.0000 0.0089
-8.500 -0.6171 0.06781 0.06626 -0.0212 1.0000 0.0090
-8.250 -0.6237 0.06251 0.06090 -0.0225 1.0000 0.0090
-8.000 -0.6263 0.05784 0.05614 -0.0228 1.0000 0.0090
-7.750 -0.6271 0.05314 0.05132 -0.0224 1.0000 0.0091
-7.500 -0.6254 0.04873 0.04677 -0.0214 1.0000 0.0092
-7.250 -0.6218 0.04458 0.04246 -0.0198 1.0000 0.0094
-7.000 -0.6357 0.03416 0.03156 -0.0145 1.0000 0.0076
-6.750 -0.6604 0.02284 0.01927 -0.0059 1.0000 0.0069
-6.500 -0.6504 0.01990 0.01593 -0.0025 1.0000 0.0074
-6.250 -0.6345 0.01836 0.01415 -0.0001 1.0000 0.0078
-6.000 -0.6179 0.01701 0.01259 0.0021 1.0000 0.0080
-5.750 -0.6001 0.01606 0.01148 0.0041 1.0000 0.0082
-5.500 -0.5713 0.01410 0.00920 0.0038 0.9981 0.0084
-5.250 -0.5409 0.01202 0.00688 0.0029 0.9950 0.0093
-5.000 -0.5080 0.01140 0.00621 0.0017 0.9912 0.0101
-4.750 -0.4743 0.01083 0.00558 0.0004 0.9866 0.0112
-4.500 -0.4393 0.01025 0.00494 -0.0013 0.9828 0.0121
-4.250 -0.4075 0.00983 0.00446 -0.0021 0.9751 0.0127
-4.000 -0.3731 0.00884 0.00334 -0.0036 0.9686 0.0149
-3.750 -0.3382 0.00856 0.00306 -0.0052 0.9572 0.0177
-3.500 -0.3028 0.00840 0.00288 -0.0069 0.9422 0.0196
-3.250 -0.2746 0.00790 0.00227 -0.0069 0.9195 0.0264
-3.000 -0.2480 0.00775 0.00202 -0.0065 0.8948 0.0315
-2.750 -0.2234 0.00758 0.00179 -0.0057 0.8705 0.0401
-2.500 -0.1991 0.00739 0.00160 -0.0048 0.8478 0.0599
-2.250 -0.1754 0.00716 0.00144 -0.0040 0.8266 0.1024
-2.000 -0.1523 0.00686 0.00129 -0.0031 0.8067 0.1670
-1.750 -0.1303 0.00646 0.00117 -0.0020 0.7881 0.2689
-1.500 -0.1094 0.00596 0.00104 -0.0007 0.7706 0.3970
-1.250 -0.0914 0.00533 0.00092 0.0012 0.7538 0.5649
-1.000 -0.0787 0.00463 0.00082 0.0045 0.7381 0.7532
-0.750 -0.0584 0.00427 0.00087 0.0065 0.7232 0.8871
-0.500 -0.0235 0.00430 0.00092 0.0051 0.7082 0.9199
-0.250 0.0131 0.00441 0.00098 0.0033 0.6935 0.9368
0.000 0.0495 0.00457 0.00107 0.0015 0.6791 0.9521
0.250 0.0837 0.00472 0.00115 0.0003 0.6647 0.9591
0.500 0.1251 0.00497 0.00133 -0.0026 0.6500 0.9659
0.750 0.1643 0.00520 0.00149 -0.0049 0.6358 0.9716
1.000 0.2071 0.00538 0.00161 -0.0082 0.6207 0.9743
1.500 0.2765 0.00573 0.00184 -0.0112 0.5897 0.9830
1.750 0.3131 0.00579 0.00186 -0.0132 0.5721 0.9840
2.000 0.3475 0.00587 0.00186 -0.0148 0.5507 0.9853
2.250 0.3804 0.00592 0.00188 -0.0160 0.5330 0.9866
2.500 0.4125 0.00601 0.00191 -0.0170 0.5105 0.9881
2.750 0.4429 0.00621 0.00193 -0.0178 0.4612 0.9899
3.000 0.4730 0.00640 0.00199 -0.0185 0.4250 0.9918
3.250 0.5020 0.00664 0.00208 -0.0190 0.3807 0.9936
3.500 0.5322 0.00693 0.00218 -0.0198 0.3254 0.9950
3.750 0.5621 0.00742 0.00232 -0.0207 0.2385 0.9963
4.000 0.5892 0.00836 0.00266 -0.0214 0.1021 0.9978
4.250 0.6176 0.00915 0.00307 -0.0220 0.0247 0.9992
4.500 0.6468 0.00944 0.00337 -0.0225 0.0184 1.0000
4.750 0.6686 0.00984 0.00386 -0.0213 0.0155 1.0000
5.000 0.6912 0.01008 0.00413 -0.0203 0.0140 1.0000
5.250 0.7135 0.01034 0.00441 -0.0194 0.0125 1.0000
5.500 0.7342 0.01085 0.00498 -0.0180 0.0112 1.0000
5.750 0.7497 0.01207 0.00638 -0.0157 0.0101 1.0000
6.000 0.7716 0.01234 0.00670 -0.0146 0.0098 1.0000
6.250 0.7925 0.01274 0.00715 -0.0134 0.0092 1.0000
6.500 0.8114 0.01342 0.00791 -0.0118 0.0087 1.0000
6.750 0.8304 0.01408 0.00863 -0.0102 0.0080 1.0000
7.000 0.8492 0.01475 0.00936 -0.0086 0.0076 1.0000
7.250 0.8675 0.01551 0.01018 -0.0069 0.0073 1.0000
7.500 0.8855 0.01626 0.01097 -0.0054 0.0068 1.0000
7.750 0.8980 0.01815 0.01303 -0.0028 0.0065 1.0000
8.000 0.9080 0.02116 0.01631 0.0001 0.0063 1.0000
8.250 0.9216 0.02300 0.01837 0.0023 0.0062 1.0000
8.500 0.9358 0.02444 0.02002 0.0045 0.0062 1.0000
8.750 0.9520 0.02527 0.02099 0.0063 0.0060 1.0000
9.000 0.9654 0.02664 0.02254 0.0084 0.0057 1.0000
9.250 0.9702 0.02951 0.02573 0.0116 0.0055 1.0000
9.500 0.9677 0.03322 0.02980 0.0156 0.0054 1.0000
9.750 0.9566 0.03769 0.03464 0.0200 0.0055 1.0000
10.000 0.9340 0.04284 0.04014 0.0249 0.0056 1.0000
10.250 0.9127 0.04584 0.04331 0.0296 0.0058 1.0000
10.500 0.8897 0.04914 0.04678 0.0327 0.0058 1.0000
10.750 0.8613 0.05405 0.05186 0.0326 0.0059 1.0000
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Polar data table (+)
Polar graphs
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