HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Reynolds number: 50,000 Max Cl/Cd: 32.6 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest2-il-50000.txt Download as CSV file: xf-tempest2-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 61% SEMISPAN 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4852 0.11093 0.10373 -0.0163 1.0000 0.3209
-9.750 -0.4620 0.10559 0.09831 -0.0158 1.0000 0.3268
-9.500 -0.5950 0.08303 0.07618 -0.0435 1.0000 0.1475
-9.250 -0.6093 0.07784 0.07103 -0.0434 1.0000 0.1382
-9.000 -0.6737 0.07367 0.06682 -0.0398 1.0000 0.1324
-8.750 -0.6771 0.06945 0.06255 -0.0379 1.0000 0.1275
-8.500 -0.6923 0.06548 0.05847 -0.0350 1.0000 0.1239
-8.250 -0.7366 0.06150 0.05389 -0.0289 1.0000 0.1174
-8.000 -0.7361 0.05773 0.04994 -0.0260 1.0000 0.1158
-7.750 -0.7379 0.05415 0.04613 -0.0226 1.0000 0.1147
-7.500 -0.7397 0.05081 0.04248 -0.0190 1.0000 0.1140
-7.250 -0.7409 0.04776 0.03899 -0.0150 1.0000 0.1147
-7.000 -0.7406 0.04504 0.03572 -0.0109 1.0000 0.1165
-6.750 -0.7287 0.04218 0.03281 -0.0087 1.0000 0.1207
-6.500 -0.7178 0.03964 0.02996 -0.0059 1.0000 0.1249
-6.250 -0.7069 0.03718 0.02692 -0.0027 1.0000 0.1299
-6.000 -0.6908 0.03503 0.02473 -0.0008 1.0000 0.1400
-5.750 -0.6729 0.03279 0.02227 0.0013 1.0000 0.1516
-5.500 -0.6551 0.03092 0.02027 0.0033 1.0000 0.1710
-5.250 -0.6351 0.02897 0.01838 0.0050 1.0000 0.1992
-5.000 -0.6163 0.02716 0.01679 0.0069 1.0000 0.2415
-4.750 -0.5985 0.02552 0.01550 0.0089 1.0000 0.2979
-4.500 -0.5821 0.02393 0.01446 0.0112 1.0000 0.3726
-4.250 -0.5719 0.02228 0.01383 0.0151 1.0000 0.4927
-4.000 -0.5567 0.02193 0.01478 0.0223 1.0000 0.7161
-3.750 -0.4772 0.02525 0.01764 0.0215 1.0000 0.8506
-3.500 -0.2734 0.02864 0.01967 -0.0039 1.0000 0.9281
-3.250 -0.0978 0.02772 0.01784 -0.0314 1.0000 0.9879
-3.000 -0.0574 0.02673 0.01661 -0.0365 1.0000 1.0000
-2.750 -0.0576 0.02630 0.01613 -0.0337 1.0000 1.0000
-2.500 -0.0591 0.02594 0.01573 -0.0307 1.0000 1.0000
-2.250 -0.0616 0.02565 0.01539 -0.0274 1.0000 1.0000
-2.000 -0.0647 0.02541 0.01510 -0.0239 1.0000 1.0000
-1.750 -0.0681 0.02522 0.01486 -0.0203 1.0000 1.0000
-1.500 -0.0714 0.02508 0.01467 -0.0166 1.0000 1.0000
-1.250 -0.0744 0.02498 0.01452 -0.0130 1.0000 1.0000
-1.000 -0.0767 0.02494 0.01440 -0.0094 1.0000 1.0000
-0.750 -0.0781 0.02493 0.01433 -0.0059 1.0000 1.0000
-0.500 -0.0784 0.02498 0.01432 -0.0025 1.0000 1.0000
-0.250 -0.0774 0.02508 0.01435 0.0007 1.0000 1.0000
0.000 -0.0751 0.02523 0.01442 0.0037 1.0000 1.0000
0.250 -0.0713 0.02543 0.01456 0.0064 1.0000 1.0000
0.500 -0.0662 0.02568 0.01473 0.0089 1.0000 1.0000
0.750 -0.0598 0.02599 0.01497 0.0112 1.0000 1.0000
1.000 -0.0524 0.02634 0.01527 0.0133 1.0000 1.0000
1.250 -0.0440 0.02675 0.01562 0.0152 1.0000 1.0000
1.500 -0.0348 0.02720 0.01603 0.0169 1.0000 1.0000
1.750 -0.0250 0.02770 0.01649 0.0185 1.0000 1.0000
2.000 0.0010 0.02859 0.01737 0.0168 0.9948 1.0000
2.250 0.0503 0.02990 0.01872 0.0106 0.9794 1.0000
2.500 0.0941 0.03104 0.01993 0.0057 0.9635 1.0000
2.750 0.1360 0.03212 0.02107 0.0014 0.9470 1.0000
3.000 0.1784 0.03314 0.02218 -0.0027 0.9300 1.0000
3.250 0.2240 0.03414 0.02331 -0.0072 0.9126 1.0000
3.500 0.2591 0.03492 0.02420 -0.0096 0.8943 1.0000
3.750 0.2938 0.03564 0.02505 -0.0118 0.8749 1.0000
4.000 0.3396 0.03631 0.02593 -0.0155 0.8554 1.0000
4.250 0.3752 0.03686 0.02665 -0.0172 0.8345 1.0000
4.500 0.4185 0.03721 0.02723 -0.0198 0.8127 1.0000
4.750 0.4594 0.03739 0.02767 -0.0216 0.7894 1.0000
5.000 0.5313 0.03652 0.02723 -0.0268 0.7643 1.0000
5.250 0.6126 0.03445 0.02571 -0.0319 0.7343 1.0000
5.500 0.6775 0.03204 0.02377 -0.0336 0.7008 1.0000
5.750 0.7515 0.02860 0.02083 -0.0352 0.6579 1.0000
6.000 0.7975 0.02616 0.01854 -0.0329 0.6012 1.0000
6.250 0.8166 0.02512 0.01739 -0.0278 0.5320 1.0000
6.500 0.8198 0.02515 0.01702 -0.0212 0.4531 1.0000
6.750 0.8183 0.02605 0.01721 -0.0148 0.3701 1.0000
7.000 0.8164 0.02775 0.01821 -0.0092 0.2938 1.0000
7.250 0.8209 0.02982 0.01973 -0.0050 0.2317 1.0000
7.500 0.8349 0.03204 0.02156 -0.0024 0.1863 1.0000
7.750 0.8583 0.03442 0.02371 -0.0013 0.1563 1.0000
8.000 0.8864 0.03719 0.02647 -0.0010 0.1378 1.0000
8.250 0.9075 0.03974 0.02907 0.0002 0.1249 1.0000
8.500 0.9212 0.04235 0.03217 0.0028 0.1184 1.0000
8.750 0.9441 0.04573 0.03550 0.0034 0.1120 1.0000
9.000 0.9439 0.04828 0.03866 0.0077 0.1090 1.0000
9.250 0.9439 0.05113 0.04194 0.0115 0.1060 1.0000
9.500 0.9427 0.05430 0.04549 0.0152 0.1047 1.0000
9.750 0.9365 0.05772 0.04926 0.0190 0.1047 1.0000
10.000 0.9254 0.06121 0.05307 0.0229 0.1054 1.0000
10.250 0.9091 0.06478 0.05692 0.0269 0.1063 1.0000
10.500 0.8881 0.06829 0.06064 0.0309 0.1073 1.0000
10.750 0.8662 0.07172 0.06420 0.0344 0.1086 1.0000
11.000 0.8431 0.07568 0.06828 0.0367 0.1096 1.0000
11.250 0.8259 0.08018 0.07284 0.0377 0.1109 1.0000
11.500 0.8203 0.08524 0.07794 0.0379 0.1120 1.0000
11.750 0.7129 0.09819 0.09096 0.0280 0.1223 1.0000
12.000 0.7063 0.10470 0.09744 0.0259 0.1247 1.0000
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