E374 (e374-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 200,000 Max Cl/Cd: 75 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e374-il-200000.txt Download as CSV file: xf-e374-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E374
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3419 0.10119 0.09789 -0.0319 1.0000 0.0455
-10.250 -0.3395 0.09763 0.09435 -0.0325 1.0000 0.0470
-10.000 -0.4466 0.09883 0.09536 -0.0352 1.0000 0.0435
-9.750 -0.4394 0.09600 0.09253 -0.0345 1.0000 0.0445
-9.500 -0.4345 0.09310 0.08966 -0.0345 1.0000 0.0459
-9.250 -0.4342 0.08952 0.08611 -0.0358 1.0000 0.0467
-9.000 -0.4356 0.08576 0.08240 -0.0374 1.0000 0.0481
-8.750 -0.4400 0.08164 0.07833 -0.0396 1.0000 0.0491
-8.500 -0.4500 0.07687 0.07363 -0.0430 1.0000 0.0505
-8.250 -0.4677 0.07215 0.06897 -0.0462 1.0000 0.0510
-8.000 -0.4843 0.06834 0.06515 -0.0461 1.0000 0.0514
-7.750 -0.5072 0.06433 0.06098 -0.0462 1.0000 0.0534
-7.500 -0.5272 0.06277 0.05916 -0.0427 1.0000 0.0542
-7.250 -0.5433 0.06137 0.05764 -0.0380 1.0000 0.0543
-6.250 -0.4760 0.03347 0.02789 -0.0433 0.9729 0.0318
-6.000 -0.4482 0.02947 0.02340 -0.0445 0.9646 0.0319
-5.750 -0.4136 0.02602 0.01955 -0.0461 0.9589 0.0308
-5.500 -0.3805 0.02290 0.01595 -0.0472 0.9519 0.0306
-5.250 -0.3435 0.02081 0.01349 -0.0488 0.9457 0.0312
-5.000 -0.3097 0.01807 0.01058 -0.0499 0.9389 0.0334
-4.750 -0.2746 0.01710 0.00957 -0.0514 0.9310 0.0400
-4.500 -0.2450 0.01560 0.00802 -0.0516 0.9212 0.0462
-4.250 -0.2146 0.01461 0.00701 -0.0521 0.9122 0.0604
-4.000 -0.1886 0.01367 0.00614 -0.0517 0.9013 0.0879
-3.750 -0.1669 0.01270 0.00548 -0.0506 0.8895 0.1547
-3.500 -0.1465 0.01185 0.00510 -0.0494 0.8783 0.2676
-3.250 -0.1286 0.01102 0.00484 -0.0477 0.8681 0.4133
-3.000 -0.1143 0.01018 0.00470 -0.0448 0.8581 0.5911
-2.750 -0.0955 0.00978 0.00485 -0.0420 0.8482 0.7505
-2.500 -0.0677 0.00980 0.00493 -0.0409 0.8404 0.8280
-2.250 -0.0359 0.00996 0.00502 -0.0408 0.8320 0.8723
-2.000 0.0024 0.01021 0.00513 -0.0420 0.8249 0.9028
-1.750 0.0458 0.01052 0.00528 -0.0443 0.8175 0.9238
-1.500 0.0972 0.01080 0.00538 -0.0485 0.8110 0.9377
-1.250 0.1486 0.01101 0.00544 -0.0530 0.8037 0.9496
-1.000 0.1964 0.01115 0.00544 -0.0569 0.7969 0.9609
-0.750 0.2425 0.01124 0.00540 -0.0607 0.7892 0.9722
-0.500 0.2896 0.01125 0.00531 -0.0648 0.7824 0.9822
-0.250 0.3388 0.01112 0.00508 -0.0695 0.7748 0.9909
0.000 0.3856 0.01096 0.00484 -0.0739 0.7679 0.9990
0.250 0.4101 0.01094 0.00477 -0.0736 0.7600 1.0000
0.500 0.4315 0.01097 0.00476 -0.0727 0.7527 1.0000
0.750 0.4530 0.01099 0.00474 -0.0718 0.7452 1.0000
1.000 0.4746 0.01104 0.00477 -0.0709 0.7380 1.0000
1.250 0.4964 0.01109 0.00478 -0.0700 0.7308 1.0000
1.500 0.5182 0.01115 0.00485 -0.0690 0.7237 1.0000
1.750 0.5402 0.01120 0.00489 -0.0681 0.7165 1.0000
2.000 0.5621 0.01128 0.00496 -0.0671 0.7091 1.0000
2.250 0.5843 0.01133 0.00500 -0.0661 0.7016 1.0000
2.500 0.6058 0.01141 0.00512 -0.0651 0.6933 1.0000
2.750 0.6285 0.01146 0.00513 -0.0640 0.6857 1.0000
3.000 0.6495 0.01153 0.00525 -0.0628 0.6761 1.0000
3.250 0.6718 0.01160 0.00532 -0.0617 0.6678 1.0000
3.500 0.6938 0.01166 0.00541 -0.0606 0.6586 1.0000
3.750 0.7151 0.01173 0.00554 -0.0593 0.6487 1.0000
4.000 0.7375 0.01179 0.00560 -0.0581 0.6392 1.0000
4.250 0.7597 0.01183 0.00565 -0.0569 0.6288 1.0000
4.500 0.7808 0.01188 0.00579 -0.0556 0.6171 1.0000
4.750 0.8022 0.01192 0.00590 -0.0542 0.6051 1.0000
5.000 0.8236 0.01196 0.00599 -0.0528 0.5921 1.0000
5.250 0.8446 0.01198 0.00606 -0.0513 0.5773 1.0000
5.500 0.8653 0.01200 0.00613 -0.0497 0.5604 1.0000
5.750 0.8857 0.01206 0.00623 -0.0481 0.5421 1.0000
6.000 0.9041 0.01212 0.00630 -0.0461 0.5147 1.0000
6.250 0.9202 0.01227 0.00639 -0.0437 0.4742 1.0000
6.500 0.9344 0.01262 0.00659 -0.0410 0.4208 1.0000
6.750 0.9453 0.01324 0.00694 -0.0379 0.3573 1.0000
7.000 0.9514 0.01422 0.00756 -0.0342 0.2836 1.0000
7.250 0.9559 0.01537 0.00832 -0.0305 0.2143 1.0000
7.500 0.9594 0.01666 0.00920 -0.0268 0.1479 1.0000
7.750 0.9589 0.01824 0.01033 -0.0225 0.0862 1.0000
8.000 0.9581 0.01984 0.01171 -0.0180 0.0580 1.0000
8.250 0.9602 0.02115 0.01299 -0.0140 0.0487 1.0000
8.500 0.9672 0.02207 0.01399 -0.0107 0.0432 1.0000
8.750 0.9712 0.02320 0.01514 -0.0072 0.0395 1.0000
9.000 0.9718 0.02495 0.01689 -0.0035 0.0369 1.0000
9.250 0.9836 0.02602 0.01809 -0.0014 0.0346 1.0000
9.500 0.9949 0.02717 0.01934 0.0006 0.0316 1.0000
9.750 1.0063 0.02859 0.02078 0.0024 0.0295 1.0000
10.000 1.0334 0.03176 0.02399 0.0024 0.0274 1.0000
10.250 1.0481 0.03308 0.02552 0.0041 0.0262 1.0000
10.500 1.0625 0.03470 0.02736 0.0056 0.0246 1.0000
10.750 1.0757 0.03650 0.02933 0.0071 0.0233 1.0000
11.000 1.0884 0.03881 0.03186 0.0086 0.0224 1.0000
11.250 1.0972 0.04142 0.03472 0.0103 0.0220 1.0000
11.500 1.1015 0.04437 0.03797 0.0123 0.0219 1.0000
11.750 1.1000 0.04750 0.04142 0.0145 0.0218 1.0000
12.000 1.0870 0.05143 0.04576 0.0172 0.0223 1.0000
12.250 1.0690 0.05574 0.05045 0.0193 0.0230 1.0000
12.500 1.0502 0.06022 0.05523 0.0206 0.0235 1.0000
12.750 1.0304 0.06486 0.06013 0.0210 0.0239 1.0000
13.000 1.0096 0.06988 0.06537 0.0205 0.0244 1.0000
13.250 0.9883 0.07520 0.07086 0.0192 0.0248 1.0000
13.500 0.9672 0.08091 0.07675 0.0172 0.0252 1.0000
13.750 0.9444 0.08734 0.08333 0.0142 0.0255 1.0000
14.000 0.9203 0.09462 0.09076 0.0102 0.0256 1.0000
14.250 0.8986 0.10226 0.09852 0.0057 0.0259 1.0000
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Polar data table (+)
Polar graphs
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