TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: TSAGI 8% AIRFOIL (tsagi8-il) Reynolds number: 50,000 Max Cl/Cd: 32.82 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi8-il-50000.txt Download as CSV file: xf-tsagi8-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5402 0.09722 0.09061 0.0082 1.0000 0.2805
-8.000 -0.5387 0.09398 0.08744 0.0086 1.0000 0.2967
-7.750 -0.5482 0.09147 0.08498 0.0087 1.0000 0.3144
-7.500 -0.5329 0.08746 0.08099 0.0109 1.0000 0.3397
-7.250 -0.5315 0.08460 0.07820 0.0130 1.0000 0.3694
-7.000 -0.5132 0.08094 0.07453 0.0161 1.0000 0.4077
-6.750 -0.5029 0.07776 0.07139 0.0191 1.0000 0.4459
-5.500 -0.5394 0.04882 0.04077 -0.0127 1.0000 0.1484
-5.250 -0.5217 0.04456 0.03640 -0.0116 1.0000 0.1420
-5.000 -0.5054 0.04073 0.03195 -0.0098 1.0000 0.1306
-4.750 -0.4882 0.03715 0.02766 -0.0076 1.0000 0.1225
-4.500 -0.4683 0.03438 0.02428 -0.0054 1.0000 0.1196
-4.250 -0.4473 0.03181 0.02118 -0.0035 1.0000 0.1205
-4.000 -0.4258 0.02939 0.01877 -0.0023 1.0000 0.1297
-3.750 -0.4011 0.02717 0.01610 -0.0008 1.0000 0.1357
-3.500 -0.3741 0.02519 0.01389 0.0002 1.0000 0.1479
-3.250 -0.1450 0.01753 0.00887 -0.0295 1.0000 1.0000
-3.000 -0.1269 0.01725 0.00821 -0.0283 1.0000 1.0000
-2.750 -0.1089 0.01701 0.00762 -0.0271 1.0000 1.0000
-2.500 -0.0911 0.01682 0.00718 -0.0257 1.0000 1.0000
-2.250 -0.0737 0.01666 0.00681 -0.0242 1.0000 1.0000
-2.000 -0.0569 0.01655 0.00652 -0.0227 1.0000 1.0000
-1.750 -0.0409 0.01647 0.00629 -0.0209 1.0000 1.0000
-1.500 -0.0260 0.01644 0.00610 -0.0190 1.0000 1.0000
-1.250 -0.0125 0.01645 0.00602 -0.0169 1.0000 1.0000
-1.000 -0.0006 0.01653 0.00602 -0.0146 1.0000 1.0000
-0.750 0.0088 0.01667 0.00610 -0.0119 1.0000 1.0000
-0.500 0.0156 0.01690 0.00627 -0.0089 1.0000 1.0000
-0.250 0.0207 0.01721 0.00651 -0.0058 1.0000 1.0000
0.000 0.0255 0.01758 0.00680 -0.0028 1.0000 1.0000
0.250 0.0309 0.01800 0.00713 -0.0001 1.0000 1.0000
0.500 0.0372 0.01846 0.00753 0.0023 1.0000 1.0000
0.750 0.0445 0.01896 0.00797 0.0044 1.0000 1.0000
1.000 0.0527 0.01950 0.00847 0.0063 1.0000 1.0000
1.250 0.0617 0.02009 0.00902 0.0079 1.0000 1.0000
1.500 0.0941 0.02088 0.00982 0.0048 0.9920 1.0000
1.750 0.1580 0.02185 0.01087 -0.0041 0.9717 1.0000
2.000 0.2175 0.02266 0.01180 -0.0117 0.9513 1.0000
2.250 0.2752 0.02333 0.01267 -0.0186 0.9305 1.0000
2.500 0.3337 0.02389 0.01344 -0.0252 0.9099 1.0000
2.750 0.3920 0.02431 0.01413 -0.0315 0.8888 1.0000
3.000 0.4468 0.02460 0.01477 -0.0366 0.8674 1.0000
3.250 0.4953 0.02483 0.01530 -0.0401 0.8454 1.0000
3.500 0.5307 0.02521 0.01595 -0.0410 0.8224 1.0000
3.750 0.5709 0.02534 0.01645 -0.0420 0.8003 1.0000
4.000 0.5970 0.02572 0.01709 -0.0407 0.7759 1.0000
4.250 0.6211 0.02607 0.01772 -0.0388 0.7508 1.0000
4.500 0.6457 0.02612 0.01807 -0.0361 0.7232 1.0000
4.750 0.6668 0.02375 0.01583 -0.0271 0.6648 1.0000
5.000 0.6776 0.02176 0.01371 -0.0179 0.5925 1.0000
5.250 0.6791 0.02069 0.01242 -0.0090 0.4740 1.0000
5.500 0.6676 0.02375 0.01312 -0.0014 0.1923 1.0000
5.750 0.6797 0.02622 0.01509 0.0013 0.1428 1.0000
6.000 0.6998 0.02844 0.01707 0.0034 0.1244 1.0000
6.250 0.7257 0.03069 0.01926 0.0047 0.1112 1.0000
6.500 0.7508 0.03281 0.02160 0.0060 0.1013 1.0000
6.750 0.7781 0.03606 0.02495 0.0069 0.0975 1.0000
7.000 0.8004 0.03902 0.02841 0.0085 0.0966 1.0000
7.250 0.8192 0.04230 0.03216 0.0103 0.0964 1.0000
7.500 0.8332 0.04560 0.03600 0.0123 0.0957 1.0000
7.750 0.8430 0.04908 0.04001 0.0144 0.0949 1.0000
8.000 0.8507 0.05299 0.04434 0.0164 0.0956 1.0000
8.250 0.8648 0.05791 0.04935 0.0174 0.0978 1.0000
8.500 0.8441 0.06181 0.05427 0.0203 0.1038 1.0000
8.750 0.8403 0.06677 0.05946 0.0213 0.1083 1.0000
9.000 0.8258 0.07159 0.06459 0.0219 0.1138 1.0000
9.250 0.7943 0.07689 0.07004 0.0214 0.1173 1.0000
9.500 0.7909 0.08238 0.07558 0.0212 0.1254 1.0000
9.750 0.7356 0.09118 0.08428 0.0128 0.1330 1.0000
10.000 0.6455 0.08878 0.08222 0.0170 0.1371 1.0000
10.250 0.5902 0.10075 0.09396 0.0066 0.1574 1.0000
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