EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 50,000 Max Cl/Cd: 27.27 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e327-il-50000-n5.txt Download as CSV file: xf-e327-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 327 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4508 0.09788 0.09113 -0.0273 1.0000 0.0487
-9.500 -0.4482 0.09389 0.08719 -0.0282 1.0000 0.0479
-9.250 -0.4534 0.08935 0.08271 -0.0302 1.0000 0.0473
-9.000 -0.4577 0.08538 0.07877 -0.0313 1.0000 0.0460
-8.750 -0.4695 0.08124 0.07465 -0.0321 1.0000 0.0453
-8.250 -0.5159 0.07319 0.06634 -0.0293 1.0000 0.0402
-8.000 -0.5229 0.07004 0.06309 -0.0274 1.0000 0.0402
-7.750 -0.5251 0.06698 0.05997 -0.0254 1.0000 0.0400
-7.500 -0.5279 0.06394 0.05682 -0.0231 1.0000 0.0399
-7.250 -0.5284 0.06105 0.05382 -0.0206 1.0000 0.0397
-7.000 -0.5287 0.05822 0.05084 -0.0179 1.0000 0.0395
-6.750 -0.5278 0.05548 0.04794 -0.0150 1.0000 0.0394
-6.500 -0.5255 0.05292 0.04523 -0.0120 1.0000 0.0390
-6.250 -0.5231 0.05044 0.04256 -0.0089 1.0000 0.0388
-6.000 -0.5210 0.04819 0.04013 -0.0055 1.0000 0.0385
-5.750 -0.5209 0.04621 0.03796 -0.0018 1.0000 0.0383
-5.500 -0.4900 0.04275 0.03402 -0.0035 0.9819 0.0382
-5.250 -0.4546 0.03952 0.03027 -0.0053 0.9603 0.0382
-5.000 -0.4159 0.03655 0.02678 -0.0073 0.9404 0.0388
-4.750 -0.3726 0.03385 0.02357 -0.0097 0.9225 0.0412
-4.500 -0.3274 0.03175 0.02129 -0.0128 0.9042 0.0452
-4.250 -0.2728 0.02952 0.01866 -0.0164 0.8872 0.0489
-4.000 -0.2152 0.02773 0.01674 -0.0208 0.8693 0.0575
-3.750 -0.1675 0.02623 0.01507 -0.0235 0.8492 0.0703
-3.500 -0.1364 0.02507 0.01386 -0.0237 0.8267 0.0885
-3.250 -0.0723 0.02217 0.01450 -0.0257 0.8120 0.7372
-3.000 0.0686 0.02517 0.01629 -0.0374 0.7896 0.9588
-2.750 0.1126 0.02471 0.01531 -0.0406 0.7655 0.9718
-2.500 0.1465 0.02433 0.01454 -0.0421 0.7437 0.9779
-2.250 0.1765 0.02411 0.01398 -0.0429 0.7247 0.9842
-2.000 0.2091 0.02377 0.01331 -0.0443 0.7072 0.9893
-1.750 0.2396 0.02355 0.01281 -0.0453 0.6906 0.9946
-1.500 0.2710 0.02329 0.01231 -0.0466 0.6752 0.9993
-1.250 0.2937 0.02326 0.01209 -0.0461 0.6612 1.0000
-1.000 0.3150 0.02328 0.01194 -0.0453 0.6481 1.0000
-0.750 0.3365 0.02332 0.01181 -0.0445 0.6361 1.0000
-0.500 0.3580 0.02337 0.01169 -0.0437 0.6253 1.0000
-0.250 0.3795 0.02346 0.01168 -0.0430 0.6135 1.0000
0.000 0.4011 0.02355 0.01167 -0.0422 0.6029 1.0000
0.250 0.4228 0.02365 0.01164 -0.0413 0.5935 1.0000
0.500 0.4442 0.02381 0.01175 -0.0406 0.5831 1.0000
0.750 0.4660 0.02395 0.01178 -0.0398 0.5745 1.0000
1.000 0.4877 0.02414 0.01193 -0.0391 0.5649 1.0000
1.250 0.5095 0.02434 0.01208 -0.0384 0.5566 1.0000
1.500 0.5310 0.02455 0.01225 -0.0376 0.5481 1.0000
1.750 0.5523 0.02480 0.01247 -0.0368 0.5399 1.0000
2.000 0.5736 0.02504 0.01270 -0.0359 0.5320 1.0000
2.250 0.5945 0.02533 0.01300 -0.0351 0.5244 1.0000
2.500 0.6153 0.02563 0.01330 -0.0342 0.5167 1.0000
2.750 0.6361 0.02593 0.01359 -0.0332 0.5098 1.0000
3.000 0.6561 0.02632 0.01403 -0.0323 0.5022 1.0000
3.250 0.6774 0.02657 0.01423 -0.0313 0.4963 1.0000
3.500 0.6959 0.02709 0.01491 -0.0303 0.4881 1.0000
3.750 0.7167 0.02737 0.01516 -0.0292 0.4823 1.0000
4.000 0.7346 0.02796 0.01588 -0.0281 0.4747 1.0000
4.250 0.7540 0.02834 0.01629 -0.0269 0.4683 1.0000
4.500 0.7724 0.02886 0.01691 -0.0256 0.4620 1.0000
4.750 0.7895 0.02944 0.01761 -0.0243 0.4549 1.0000
5.000 0.8103 0.02971 0.01786 -0.0231 0.4498 1.0000
5.250 0.8233 0.03062 0.01901 -0.0215 0.4419 1.0000
5.500 0.8420 0.03103 0.01947 -0.0201 0.4362 1.0000
5.750 0.8561 0.03179 0.02037 -0.0184 0.4295 1.0000
6.000 0.8710 0.03246 0.02116 -0.0167 0.4229 1.0000
6.250 0.8908 0.03276 0.02150 -0.0153 0.4179 1.0000
6.500 0.8972 0.03396 0.02295 -0.0129 0.4098 1.0000
6.750 0.9155 0.03430 0.02334 -0.0113 0.4044 1.0000
7.000 0.9215 0.03546 0.02470 -0.0088 0.3972 1.0000
7.250 0.9343 0.03607 0.02544 -0.0066 0.3909 1.0000
7.500 0.9466 0.03673 0.02621 -0.0045 0.3850 1.0000
7.750 0.9477 0.03796 0.02764 -0.0013 0.3775 1.0000
8.000 0.9703 0.03791 0.02761 0.0001 0.3723 1.0000
8.250 0.9555 0.03992 0.02986 0.0048 0.3644 1.0000
8.500 0.9726 0.04007 0.03010 0.0067 0.3585 1.0000
8.750 0.9599 0.04181 0.03199 0.0112 0.3515 1.0000
9.000 0.9631 0.04262 0.03291 0.0144 0.3449 1.0000
9.250 0.9654 0.04351 0.03389 0.0175 0.3386 1.0000
9.500 0.9402 0.04590 0.03636 0.0225 0.3313 1.0000
9.750 0.9732 0.04512 0.03567 0.0232 0.3253 1.0000
10.000 0.8905 0.05151 0.04201 0.0300 0.3171 1.0000
10.250 0.9636 0.04780 0.03852 0.0295 0.3115 1.0000
10.500 0.8570 0.05870 0.04928 0.0316 0.3000 1.0000
10.750 0.8959 0.05658 0.04733 0.0335 0.2953 1.0000
11.000 0.8508 0.06427 0.05498 0.0319 0.2835 1.0000
11.250 0.8145 0.07199 0.06267 0.0296 0.2710 1.0000
11.500 0.8550 0.06887 0.05977 0.0322 0.2676 1.0000
11.750 0.8178 0.07714 0.06798 0.0294 0.2550 1.0000
12.250 0.8246 0.08187 0.07292 0.0292 0.2395 1.0000
12.750 0.7961 0.09257 0.08366 0.0258 0.2204 1.0000
13.000 0.8008 0.09498 0.08617 0.0255 0.2128 1.0000
13.500 0.8059 0.10052 0.09189 0.0244 0.1979 1.0000
14.000 0.8100 0.10641 0.09794 0.0230 0.1833 1.0000
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Polar data table (+)
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