EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 336 AIRFOIL (e336-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.03 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e336-il-1000000.txt Download as CSV file: xf-e336-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 336 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4921 0.06152 0.05916 -0.0314 0.7628 0.0088
-8.000 -0.4996 0.05830 0.05574 -0.0290 0.7360 0.0088
-7.750 -0.5033 0.05505 0.05232 -0.0265 0.7139 0.0090
-7.500 -0.5036 0.05185 0.04894 -0.0241 0.6953 0.0090
-7.250 -0.5020 0.04854 0.04544 -0.0215 0.6776 0.0093
-7.000 -0.4979 0.04523 0.04192 -0.0188 0.6632 0.0095
-6.750 -0.4917 0.04173 0.03819 -0.0159 0.6504 0.0098
-6.500 -0.4844 0.03566 0.03161 -0.0107 0.6406 0.0104
-6.250 -0.4875 0.03072 0.02629 -0.0063 0.6305 0.0107
-6.000 -0.4722 0.02923 0.02468 -0.0047 0.6173 0.0108
-5.750 -0.4559 0.02780 0.02308 -0.0030 0.6048 0.0110
-5.500 -0.4383 0.02641 0.02152 -0.0013 0.5932 0.0112
-5.250 -0.4199 0.02488 0.01980 0.0004 0.5824 0.0116
-5.000 -0.4004 0.02312 0.01776 0.0023 0.5722 0.0124
-4.250 -0.3283 0.01521 0.00857 0.0076 0.5443 0.0081
-4.000 -0.3010 0.01372 0.00701 0.0079 0.5353 0.0074
-3.500 -0.2509 0.01206 0.00511 0.0095 0.5174 0.0068
-3.250 -0.2273 0.01152 0.00448 0.0105 0.5088 0.0067
-3.000 -0.2031 0.01110 0.00400 0.0114 0.5007 0.0067
-2.750 -0.1792 0.01075 0.00358 0.0124 0.4926 0.0069
-2.500 -0.1544 0.01045 0.00324 0.0131 0.4847 0.0071
-2.250 -0.1298 0.01022 0.00294 0.0139 0.4767 0.0073
-2.000 -0.1043 0.01001 0.00269 0.0145 0.4687 0.0079
-1.750 -0.0798 0.00979 0.00241 0.0153 0.4604 0.0097
-1.500 -0.0560 0.00945 0.00215 0.0163 0.4531 0.0330
-1.250 -0.0324 0.00921 0.00204 0.0171 0.4451 0.0780
-1.000 -0.0092 0.00889 0.00194 0.0180 0.4378 0.1458
-0.750 -0.0038 0.00758 0.00170 0.0221 0.4306 0.4697
-0.500 -0.0097 0.00621 0.00144 0.0290 0.4249 0.7614
-0.250 0.0070 0.00642 0.00201 0.0323 0.4157 0.8923
0.000 0.0332 0.00696 0.00254 0.0335 0.4067 0.9115
0.250 0.0622 0.00732 0.00283 0.0338 0.3973 0.9186
0.500 0.0972 0.00780 0.00325 0.0329 0.3887 0.9248
0.750 0.1223 0.00807 0.00345 0.0338 0.3812 0.9312
1.000 0.1714 0.00854 0.00385 0.0298 0.3728 0.9335
1.250 0.2093 0.00874 0.00397 0.0277 0.3665 0.9346
1.500 0.2395 0.00878 0.00397 0.0272 0.3621 0.9354
1.750 0.2693 0.00884 0.00397 0.0267 0.3580 0.9362
2.000 0.2976 0.00890 0.00398 0.0266 0.3535 0.9373
2.250 0.3250 0.00893 0.00399 0.0266 0.3508 0.9385
2.500 0.3492 0.00894 0.00398 0.0273 0.3484 0.9403
2.750 0.3494 0.00886 0.00390 0.0331 0.3466 0.9456
3.000 0.3776 0.00885 0.00386 0.0330 0.3437 0.9462
3.250 0.4053 0.00888 0.00385 0.0329 0.3406 0.9468
3.500 0.4337 0.00895 0.00389 0.0326 0.3375 0.9474
3.750 0.4627 0.00897 0.00391 0.0322 0.3357 0.9480
4.000 0.4908 0.00899 0.00394 0.0321 0.3333 0.9486
4.250 0.5180 0.00903 0.00397 0.0321 0.3309 0.9492
4.500 0.5450 0.00909 0.00402 0.0321 0.3282 0.9499
4.750 0.5717 0.00919 0.00410 0.0321 0.3249 0.9508
5.000 0.5970 0.00928 0.00418 0.0325 0.3220 0.9518
5.250 0.6227 0.00928 0.00421 0.0328 0.3199 0.9526
5.500 0.6472 0.00929 0.00425 0.0333 0.3175 0.9537
5.750 0.6706 0.00932 0.00428 0.0341 0.3147 0.9549
6.000 0.6925 0.00936 0.00434 0.0351 0.3121 0.9564
6.250 0.7118 0.00946 0.00441 0.0367 0.3083 0.9582
6.500 0.7326 0.00949 0.00447 0.0379 0.3057 0.9594
6.750 0.7582 0.00946 0.00449 0.0382 0.3030 0.9602
7.000 0.7855 0.00947 0.00453 0.0381 0.2993 0.9608
7.250 0.8122 0.00953 0.00459 0.0380 0.2949 0.9614
7.500 0.8386 0.00963 0.00470 0.0380 0.2905 0.9621
7.750 0.8664 0.00964 0.00476 0.0378 0.2865 0.9626
8.000 0.8932 0.00969 0.00483 0.0377 0.2810 0.9633
8.250 0.9197 0.00979 0.00495 0.0377 0.2756 0.9642
8.500 0.9465 0.00986 0.00504 0.0376 0.2685 0.9651
8.750 0.9716 0.00998 0.00516 0.0378 0.2609 0.9660
9.000 0.9956 0.01013 0.00530 0.0382 0.2515 0.9671
9.250 1.0186 0.01030 0.00547 0.0388 0.2423 0.9684
9.500 1.0398 0.01050 0.00567 0.0397 0.2336 0.9699
9.750 1.0595 0.01071 0.00587 0.0409 0.2243 0.9715
10.000 1.0795 0.01092 0.00608 0.0420 0.2147 0.9730
10.250 1.1039 0.01121 0.00636 0.0421 0.2038 0.9740
10.500 1.1279 0.01157 0.00670 0.0421 0.1909 0.9750
10.750 1.1510 0.01200 0.00709 0.0423 0.1758 0.9761
11.000 1.1731 0.01248 0.00753 0.0425 0.1609 0.9774
11.250 1.1940 0.01304 0.00804 0.0429 0.1453 0.9790
11.500 1.2127 0.01363 0.00858 0.0436 0.1309 0.9811
11.750 1.2266 0.01418 0.00910 0.0454 0.1188 0.9840
12.000 1.2460 0.01499 0.00985 0.0455 0.1034 0.9854
12.250 1.2671 0.01579 0.01061 0.0452 0.0915 0.9865
12.500 1.2856 0.01671 0.01150 0.0451 0.0794 0.9880
12.750 1.3029 0.01766 0.01243 0.0450 0.0700 0.9899
13.000 1.3181 0.01868 0.01348 0.0450 0.0619 0.9923
13.250 1.3316 0.01992 0.01473 0.0448 0.0550 0.9947
13.500 1.3449 0.02160 0.01642 0.0435 0.0476 0.9971
13.750 1.3564 0.02367 0.01851 0.0417 0.0415 0.9993
14.000 1.3486 0.02529 0.02019 0.0442 0.0393 1.0000
14.250 1.3348 0.02732 0.02227 0.0471 0.0370 1.0000
14.500 1.3271 0.03003 0.02502 0.0478 0.0338 1.0000
14.750 1.3249 0.03250 0.02756 0.0479 0.0320 1.0000
15.000 1.3150 0.03587 0.03096 0.0478 0.0289 1.0000
15.250 1.3082 0.03903 0.03419 0.0476 0.0268 1.0000
15.500 1.3009 0.04230 0.03754 0.0472 0.0253 1.0000
15.750 1.2876 0.04629 0.04157 0.0467 0.0231 1.0000
16.000 1.2793 0.04981 0.04518 0.0461 0.0228 1.0000
16.250 1.2720 0.05331 0.04877 0.0454 0.0225 1.0000
16.500 1.2619 0.05722 0.05274 0.0445 0.0205 1.0000
16.750 1.2504 0.06145 0.05703 0.0435 0.0194 1.0000
17.000 1.2397 0.06565 0.06130 0.0423 0.0182 1.0000
17.250 1.2311 0.06965 0.06536 0.0411 0.0168 1.0000
17.500 1.2205 0.07403 0.06980 0.0398 0.0157 1.0000
17.750 1.2117 0.07824 0.07410 0.0385 0.0155 1.0000
18.000 1.2025 0.08254 0.07846 0.0371 0.0143 1.0000
18.250 1.1947 0.08672 0.08271 0.0357 0.0136 1.0000
18.500 1.1864 0.09097 0.08702 0.0342 0.0130 1.0000
18.750 1.1770 0.09549 0.09161 0.0325 0.0125 1.0000
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