TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 500,000 Max Cl/Cd: 76.53 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi12-il-500000-n5.txt Download as CSV file: xf-tsagi12-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 12% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7633 0.09342 0.09089 -0.0263 1.0000 0.0070
-14.250 -0.8555 0.07124 0.06861 -0.0389 1.0000 0.0066
-14.000 -0.9230 0.05014 0.04712 -0.0560 1.0000 0.0062
-13.750 -0.9506 0.04385 0.04059 -0.0588 1.0000 0.0061
-13.500 -0.9609 0.04065 0.03723 -0.0584 1.0000 0.0063
-13.250 -0.9765 0.03748 0.03385 -0.0566 1.0000 0.0063
-13.000 -0.9818 0.03538 0.03159 -0.0543 1.0000 0.0065
-12.750 -0.9872 0.03344 0.02947 -0.0513 1.0000 0.0065
-12.500 -0.9932 0.03155 0.02740 -0.0476 1.0000 0.0066
-12.250 -0.9941 0.03009 0.02577 -0.0441 1.0000 0.0067
-12.000 -0.9957 0.02868 0.02418 -0.0401 1.0000 0.0068
-11.750 -0.9940 0.02755 0.02289 -0.0362 1.0000 0.0069
-11.500 -0.9870 0.02656 0.02175 -0.0331 1.0000 0.0071
-11.250 -0.9805 0.02540 0.02044 -0.0299 1.0000 0.0072
-11.000 -0.9741 0.02421 0.01911 -0.0266 1.0000 0.0074
-10.750 -0.9637 0.02329 0.01810 -0.0239 1.0000 0.0077
-10.500 -0.9517 0.02247 0.01718 -0.0214 1.0000 0.0080
-10.250 -0.9378 0.02181 0.01644 -0.0191 1.0000 0.0084
-10.000 -0.9250 0.02105 0.01558 -0.0166 1.0000 0.0086
-9.750 -0.9115 0.02037 0.01479 -0.0141 1.0000 0.0089
-9.500 -0.8927 0.01961 0.01391 -0.0127 0.9989 0.0093
-9.250 -0.8645 0.01878 0.01295 -0.0133 0.9932 0.0097
-9.000 -0.8363 0.01795 0.01200 -0.0139 0.9869 0.0101
-8.750 -0.8090 0.01706 0.01102 -0.0143 0.9795 0.0109
-8.500 -0.7773 0.01644 0.01035 -0.0155 0.9731 0.0119
-8.250 -0.7450 0.01588 0.00971 -0.0168 0.9655 0.0130
-8.000 -0.7111 0.01530 0.00902 -0.0184 0.9572 0.0138
-7.750 -0.6753 0.01463 0.00833 -0.0204 0.9476 0.0157
-7.500 -0.6388 0.01414 0.00778 -0.0226 0.9344 0.0175
-7.000 -0.5728 0.01327 0.00677 -0.0252 0.8981 0.0219
-6.750 -0.5450 0.01300 0.00636 -0.0252 0.8744 0.0242
-6.500 -0.5203 0.01280 0.00601 -0.0245 0.8499 0.0259
-6.250 -0.4979 0.01251 0.00560 -0.0234 0.8278 0.0284
-6.000 -0.4754 0.01226 0.00526 -0.0223 0.8073 0.0308
-5.750 -0.4524 0.01205 0.00494 -0.0213 0.7906 0.0327
-5.500 -0.4288 0.01187 0.00463 -0.0204 0.7764 0.0345
-5.250 -0.4057 0.01161 0.00432 -0.0194 0.7638 0.0378
-5.000 -0.3822 0.01140 0.00406 -0.0186 0.7517 0.0415
-4.750 -0.3584 0.01121 0.00382 -0.0177 0.7397 0.0454
-4.500 -0.3343 0.01101 0.00362 -0.0170 0.7287 0.0531
-4.250 -0.3102 0.01084 0.00343 -0.0162 0.7180 0.0612
-4.000 -0.2854 0.01075 0.00326 -0.0155 0.7076 0.0674
-3.750 -0.2611 0.01058 0.00306 -0.0148 0.6971 0.0735
-3.500 -0.2364 0.01046 0.00288 -0.0141 0.6872 0.0791
-3.000 -0.1870 0.01021 0.00255 -0.0128 0.6693 0.0902
-2.750 -0.1623 0.01009 0.00240 -0.0122 0.6605 0.0978
-2.500 -0.1384 0.00990 0.00227 -0.0114 0.6514 0.1192
-2.250 -0.1146 0.00970 0.00216 -0.0106 0.6435 0.1528
-2.000 -0.0907 0.00952 0.00205 -0.0099 0.6353 0.1841
-1.750 -0.0668 0.00934 0.00196 -0.0091 0.6276 0.2178
-1.500 -0.0443 0.00909 0.00186 -0.0081 0.6194 0.2719
-1.250 -0.0247 0.00864 0.00175 -0.0066 0.6115 0.3686
-1.000 -0.0080 0.00815 0.00164 -0.0044 0.6033 0.4861
-0.750 0.0016 0.00749 0.00154 -0.0006 0.5960 0.6355
-0.500 0.0163 0.00711 0.00150 0.0024 0.5881 0.7343
-0.250 0.0429 0.00688 0.00157 0.0029 0.5792 0.8203
0.000 0.0806 0.00691 0.00165 0.0009 0.5691 0.8628
0.250 0.1233 0.00702 0.00175 -0.0023 0.5583 0.8890
0.500 0.1626 0.00715 0.00186 -0.0047 0.5467 0.9063
0.750 0.2060 0.00735 0.00201 -0.0080 0.5342 0.9179
1.000 0.2458 0.00767 0.00228 -0.0104 0.5219 0.9302
1.250 0.2789 0.00796 0.00251 -0.0112 0.5094 0.9390
1.500 0.3153 0.00819 0.00267 -0.0130 0.4966 0.9424
1.750 0.3448 0.00835 0.00277 -0.0134 0.4850 0.9469
2.000 0.3681 0.00845 0.00283 -0.0124 0.4740 0.9511
2.250 0.4001 0.00856 0.00289 -0.0134 0.4639 0.9522
2.750 0.4619 0.00880 0.00305 -0.0150 0.4445 0.9550
3.000 0.4912 0.00892 0.00314 -0.0155 0.4364 0.9570
3.250 0.5186 0.00903 0.00324 -0.0155 0.4282 0.9598
3.500 0.5407 0.00915 0.00335 -0.0143 0.4213 0.9638
3.750 0.5730 0.00927 0.00346 -0.0154 0.4130 0.9648
4.000 0.6044 0.00940 0.00358 -0.0164 0.4031 0.9661
4.250 0.6343 0.00955 0.00370 -0.0170 0.3924 0.9676
4.500 0.6637 0.00966 0.00383 -0.0175 0.3833 0.9694
4.750 0.6909 0.00979 0.00397 -0.0176 0.3761 0.9717
5.000 0.7132 0.00992 0.00412 -0.0165 0.3686 0.9751
5.250 0.7440 0.01005 0.00426 -0.0174 0.3594 0.9760
5.500 0.7736 0.01022 0.00441 -0.0180 0.3407 0.9771
5.750 0.8020 0.01048 0.00458 -0.0185 0.3132 0.9785
6.000 0.8277 0.01088 0.00482 -0.0185 0.2741 0.9805
6.250 0.8492 0.01150 0.00518 -0.0178 0.2220 0.9829
6.500 0.8691 0.01215 0.00563 -0.0168 0.1772 0.9856
6.750 0.8934 0.01297 0.00617 -0.0170 0.1220 0.9871
7.250 0.9397 0.01445 0.00729 -0.0167 0.0520 0.9908
7.500 0.9613 0.01520 0.00791 -0.0162 0.0299 0.9930
7.750 0.9855 0.01575 0.00847 -0.0161 0.0223 0.9948
8.000 1.0119 0.01625 0.00900 -0.0164 0.0180 0.9962
8.250 1.0371 0.01678 0.00955 -0.0166 0.0156 0.9978
8.500 1.0615 0.01739 0.01021 -0.0166 0.0137 0.9993
8.750 1.0816 0.01788 0.01077 -0.0157 0.0126 1.0000
9.000 1.0930 0.01838 0.01132 -0.0130 0.0117 1.0000
9.250 1.1025 0.01894 0.01193 -0.0100 0.0112 1.0000
9.500 1.1091 0.01958 0.01263 -0.0065 0.0106 1.0000
9.750 1.1097 0.02038 0.01349 -0.0020 0.0099 1.0000
10.000 1.1099 0.02085 0.01403 0.0027 0.0097 1.0000
10.250 1.1108 0.02138 0.01462 0.0071 0.0093 1.0000
10.500 1.1122 0.02205 0.01536 0.0111 0.0090 1.0000
10.750 1.1139 0.02286 0.01624 0.0146 0.0087 1.0000
11.000 1.1160 0.02380 0.01725 0.0178 0.0084 1.0000
11.250 1.1194 0.02482 0.01833 0.0205 0.0081 1.0000
11.500 1.1217 0.02603 0.01961 0.0229 0.0078 1.0000
11.750 1.1234 0.02745 0.02109 0.0251 0.0075 1.0000
12.000 1.1249 0.02901 0.02272 0.0269 0.0074 1.0000
12.250 1.1213 0.03114 0.02496 0.0287 0.0071 1.0000
12.500 1.1220 0.03306 0.02697 0.0300 0.0070 1.0000
12.750 1.1245 0.03494 0.02895 0.0310 0.0068 1.0000
13.000 1.1261 0.03699 0.03109 0.0318 0.0067 1.0000
13.250 1.1263 0.03926 0.03347 0.0325 0.0065 1.0000
13.500 1.1265 0.04162 0.03592 0.0331 0.0063 1.0000
13.750 1.1259 0.04412 0.03851 0.0334 0.0061 1.0000
14.000 1.1242 0.04680 0.04130 0.0337 0.0060 1.0000
14.250 1.1228 0.04954 0.04413 0.0338 0.0060 1.0000
14.500 1.1234 0.05214 0.04681 0.0337 0.0059 1.0000
14.750 1.1209 0.05518 0.04995 0.0334 0.0058 1.0000
15.000 1.1173 0.05844 0.05331 0.0331 0.0057 1.0000
15.250 1.1143 0.06176 0.05672 0.0325 0.0056 1.0000
15.500 1.1143 0.06486 0.05990 0.0317 0.0054 1.0000
15.750 1.1106 0.06844 0.06358 0.0308 0.0053 1.0000
16.000 1.1040 0.07237 0.06765 0.0301 0.0055 1.0000
16.250 1.1016 0.07610 0.07142 0.0287 0.0052 1.0000
16.500 1.0956 0.08024 0.07565 0.0274 0.0051 1.0000
16.750 1.0904 0.08433 0.07984 0.0261 0.0051 1.0000
17.000 1.0811 0.08910 0.08471 0.0246 0.0050 1.0000
17.250 1.0740 0.09366 0.08938 0.0230 0.0050 1.0000
17.500 1.0674 0.09834 0.09417 0.0212 0.0049 1.0000
17.750 1.0597 0.10323 0.09919 0.0192 0.0048 1.0000
18.000 1.0512 0.10841 0.10450 0.0171 0.0048 1.0000
18.250 1.0410 0.11392 0.11013 0.0148 0.0048 1.0000
18.500 1.0323 0.11937 0.11569 0.0124 0.0047 1.0000
18.750 1.0205 0.12549 0.12194 0.0096 0.0047 1.0000
19.000 1.0104 0.13141 0.12798 0.0068 0.0047 1.0000
19.250 0.9981 0.13799 0.13469 0.0036 0.0047 1.0000
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Polar data table (+)
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