EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 200,000 Max Cl/Cd: 44.42 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e521-il-200000.txt Download as CSV file: xf-e521-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 521 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7198 0.10012 0.09666 -0.0189 1.0000 0.0225
-14.750 -0.9025 0.08019 0.07590 -0.0302 1.0000 0.0177
-14.500 -0.9208 0.07378 0.06929 -0.0337 1.0000 0.0177
-14.250 -0.9152 0.07180 0.06738 -0.0350 1.0000 0.0189
-14.000 -0.9373 0.06557 0.06088 -0.0377 1.0000 0.0188
-13.750 -0.9601 0.05939 0.05435 -0.0392 1.0000 0.0182
-13.500 -0.9562 0.05779 0.05276 -0.0399 1.0000 0.0195
-13.250 -0.9636 0.05453 0.04934 -0.0403 1.0000 0.0202
-13.000 -0.9737 0.05080 0.04537 -0.0401 1.0000 0.0204
-12.750 -0.9791 0.04774 0.04209 -0.0396 1.0000 0.0208
-12.500 -0.9829 0.04487 0.03898 -0.0387 1.0000 0.0214
-12.250 -0.9839 0.04228 0.03613 -0.0376 1.0000 0.0220
-12.000 -0.9826 0.04017 0.03377 -0.0363 1.0000 0.0227
-11.750 -0.9763 0.03649 0.02990 -0.0351 1.0000 0.0242
-11.500 -0.9685 0.03484 0.02823 -0.0341 1.0000 0.0258
-11.250 -0.9605 0.03350 0.02680 -0.0330 1.0000 0.0279
-11.000 -0.9515 0.03228 0.02539 -0.0316 1.0000 0.0302
-10.750 -0.9383 0.02981 0.02287 -0.0306 1.0000 0.0332
-10.500 -0.9275 0.02863 0.02167 -0.0294 1.0000 0.0364
-10.250 -0.9147 0.02769 0.02057 -0.0281 1.0000 0.0400
-10.000 -0.9022 0.02582 0.01871 -0.0269 1.0000 0.0442
-9.750 -0.8887 0.02488 0.01773 -0.0257 1.0000 0.0489
-9.500 -0.8765 0.02359 0.01641 -0.0242 1.0000 0.0542
-9.250 -0.8647 0.02271 0.01553 -0.0226 1.0000 0.0605
-9.000 -0.8577 0.02174 0.01458 -0.0202 1.0000 0.0670
-8.750 -0.8677 0.02145 0.01430 -0.0146 1.0000 0.0711
-8.500 -0.8620 0.02072 0.01354 -0.0119 0.9964 0.0793
-8.250 -0.8347 0.01964 0.01252 -0.0133 0.9898 0.0961
-8.000 -0.8052 0.01867 0.01157 -0.0149 0.9843 0.1175
-7.750 -0.7746 0.01777 0.01075 -0.0167 0.9798 0.1436
-7.500 -0.7472 0.01698 0.01007 -0.0178 0.9742 0.1713
-7.250 -0.7176 0.01621 0.00945 -0.0193 0.9699 0.2030
-7.000 -0.6911 0.01556 0.00892 -0.0201 0.9649 0.2359
-6.750 -0.6658 0.01499 0.00844 -0.0204 0.9593 0.2715
-6.500 -0.6381 0.01439 0.00800 -0.0213 0.9552 0.3110
-6.250 -0.6166 0.01394 0.00768 -0.0207 0.9497 0.3488
-6.000 -0.5940 0.01352 0.00739 -0.0203 0.9443 0.3897
-5.750 -0.5688 0.01310 0.00712 -0.0202 0.9404 0.4327
-5.500 -0.5496 0.01281 0.00697 -0.0189 0.9349 0.4724
-5.250 -0.5273 0.01255 0.00686 -0.0180 0.9299 0.5138
-5.000 -0.5020 0.01238 0.00683 -0.0175 0.9262 0.5545
-4.750 -0.4797 0.01237 0.00693 -0.0164 0.9215 0.5911
-4.500 -0.4557 0.01245 0.00706 -0.0156 0.9167 0.6223
-4.250 -0.4287 0.01262 0.00724 -0.0151 0.9130 0.6481
-4.000 -0.4024 0.01287 0.00748 -0.0144 0.9091 0.6689
-3.750 -0.3780 0.01316 0.00774 -0.0136 0.9039 0.6861
-3.500 -0.3515 0.01344 0.00797 -0.0129 0.8997 0.7011
-3.250 -0.3239 0.01374 0.00822 -0.0123 0.8963 0.7143
-3.000 -0.3004 0.01404 0.00850 -0.0114 0.8904 0.7262
-2.750 -0.2751 0.01428 0.00868 -0.0106 0.8857 0.7381
-2.500 -0.2472 0.01458 0.00895 -0.0099 0.8821 0.7468
-2.250 -0.2233 0.01484 0.00921 -0.0090 0.8760 0.7559
-2.000 -0.1988 0.01498 0.00930 -0.0081 0.8709 0.7665
-1.750 -0.1711 0.01524 0.00955 -0.0072 0.8671 0.7728
-1.500 -0.1486 0.01539 0.00968 -0.0062 0.8600 0.7823
-1.250 -0.1219 0.01556 0.00985 -0.0052 0.8552 0.7889
-1.000 -0.0985 0.01567 0.00994 -0.0042 0.8493 0.7973
-0.750 -0.0732 0.01579 0.01007 -0.0032 0.8431 0.8039
-0.500 -0.0483 0.01578 0.01002 -0.0021 0.8386 0.8116
-0.250 -0.0244 0.01591 0.01018 -0.0011 0.8306 0.8176
0.000 0.0000 0.01582 0.01006 0.0000 0.8253 0.8253
0.250 0.0244 0.01591 0.01018 0.0011 0.8176 0.8306
0.500 0.0483 0.01578 0.01002 0.0021 0.8116 0.8386
0.750 0.0732 0.01580 0.01007 0.0032 0.8039 0.8431
1.000 0.0985 0.01567 0.00994 0.0042 0.7973 0.8493
1.250 0.1219 0.01556 0.00985 0.0052 0.7889 0.8552
1.500 0.1486 0.01539 0.00969 0.0062 0.7823 0.8600
1.750 0.1711 0.01524 0.00955 0.0072 0.7728 0.8671
2.000 0.1988 0.01498 0.00930 0.0081 0.7665 0.8709
2.250 0.2234 0.01484 0.00921 0.0090 0.7559 0.8760
2.500 0.2472 0.01457 0.00895 0.0099 0.7467 0.8821
2.750 0.2751 0.01428 0.00868 0.0106 0.7381 0.8857
3.000 0.3005 0.01404 0.00850 0.0114 0.7262 0.8904
3.250 0.3240 0.01374 0.00823 0.0123 0.7142 0.8963
3.500 0.3515 0.01344 0.00798 0.0129 0.7012 0.8996
3.750 0.3781 0.01316 0.00775 0.0135 0.6861 0.9039
4.000 0.4024 0.01287 0.00748 0.0144 0.6689 0.9091
4.250 0.4287 0.01262 0.00724 0.0151 0.6481 0.9130
4.500 0.4557 0.01246 0.00705 0.0155 0.6224 0.9167
4.750 0.4797 0.01237 0.00693 0.0164 0.5912 0.9215
5.000 0.5020 0.01238 0.00683 0.0175 0.5547 0.9262
5.250 0.5273 0.01255 0.00686 0.0180 0.5138 0.9299
5.500 0.5497 0.01281 0.00697 0.0189 0.4727 0.9348
5.750 0.5688 0.01311 0.00712 0.0202 0.4327 0.9403
6.000 0.5940 0.01352 0.00739 0.0203 0.3897 0.9443
6.250 0.6166 0.01394 0.00768 0.0207 0.3488 0.9497
6.500 0.6381 0.01439 0.00800 0.0213 0.3110 0.9552
6.750 0.6657 0.01499 0.00844 0.0205 0.2715 0.9593
7.000 0.6911 0.01556 0.00892 0.0201 0.2362 0.9649
7.250 0.7176 0.01621 0.00945 0.0193 0.2032 0.9699
7.500 0.7472 0.01698 0.01007 0.0178 0.1714 0.9741
7.750 0.7747 0.01777 0.01075 0.0167 0.1433 0.9798
8.000 0.8052 0.01867 0.01156 0.0149 0.1175 0.9843
8.250 0.8347 0.01963 0.01251 0.0133 0.0959 0.9897
8.500 0.8619 0.02073 0.01354 0.0119 0.0791 0.9965
8.750 0.8677 0.02146 0.01430 0.0146 0.0710 1.0000
9.000 0.8576 0.02173 0.01457 0.0202 0.0670 1.0000
9.250 0.8645 0.02270 0.01552 0.0227 0.0604 1.0000
9.500 0.8763 0.02358 0.01640 0.0243 0.0542 1.0000
9.750 0.8885 0.02491 0.01775 0.0257 0.0491 1.0000
10.000 0.9021 0.02582 0.01871 0.0269 0.0443 1.0000
10.250 0.9141 0.02763 0.02051 0.0282 0.0400 1.0000
10.500 0.9275 0.02866 0.02170 0.0294 0.0366 1.0000
10.750 0.9381 0.02981 0.02287 0.0306 0.0332 1.0000
11.000 0.9513 0.03227 0.02538 0.0317 0.0302 1.0000
11.250 0.9611 0.03361 0.02691 0.0330 0.0280 1.0000
11.500 0.9693 0.03497 0.02838 0.0342 0.0260 1.0000
11.750 0.9762 0.03651 0.02992 0.0352 0.0241 1.0000
12.000 0.9827 0.04017 0.03376 0.0363 0.0227 1.0000
12.250 0.9843 0.04223 0.03607 0.0376 0.0221 1.0000
12.500 0.9839 0.04483 0.03893 0.0387 0.0215 1.0000
12.750 0.9799 0.04753 0.04186 0.0396 0.0206 1.0000
13.000 0.9738 0.05078 0.04535 0.0401 0.0204 1.0000
13.250 0.9694 0.05349 0.04821 0.0402 0.0194 1.0000
13.500 0.9627 0.05679 0.05170 0.0399 0.0190 1.0000
13.750 0.9490 0.06127 0.05641 0.0391 0.0189 1.0000
14.000 0.9268 0.06722 0.06265 0.0371 0.0193 1.0000
14.250 0.9192 0.07121 0.06676 0.0352 0.0188 1.0000
14.500 0.9104 0.07561 0.07125 0.0328 0.0182 1.0000
14.750 0.8595 0.08847 0.08453 0.0251 0.0196 1.0000
15.000 0.8187 0.10119 0.09750 0.0168 0.0209 1.0000
15.250 0.7790 0.11514 0.11161 0.0080 0.0219 1.0000
15.500 0.7505 0.12700 0.12350 0.0015 0.0228 1.0000
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