GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Reynolds number: 200,000 Max Cl/Cd: 72.53 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe278-il-200000.txt Download as CSV file: xf-goe278-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 278 (DAIMLER IX) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2735 0.08738 0.08405 -0.0287 1.0000 0.0300
-8.250 -0.2734 0.08452 0.08123 -0.0282 1.0000 0.0305
-8.000 -0.3674 0.09434 0.09089 -0.0272 1.0000 0.0290
-7.750 -0.3620 0.09100 0.08757 -0.0254 1.0000 0.0294
-7.500 -0.3623 0.08846 0.08509 -0.0245 1.0000 0.0298
-7.250 -0.3637 0.08611 0.08279 -0.0240 1.0000 0.0302
-7.000 -0.3669 0.08392 0.08065 -0.0233 1.0000 0.0307
-6.750 -0.3700 0.08177 0.07853 -0.0226 1.0000 0.0313
-6.500 -0.3718 0.07949 0.07629 -0.0223 1.0000 0.0320
-6.250 -0.3708 0.07701 0.07383 -0.0228 1.0000 0.0330
-6.000 -0.3652 0.07430 0.07110 -0.0247 1.0000 0.0342
-5.750 -0.3432 0.07166 0.06828 -0.0325 1.0000 0.0354
-5.500 -0.3258 0.06887 0.06529 -0.0357 1.0000 0.0357
-5.250 -0.3236 0.06367 0.06018 -0.0345 1.0000 0.0362
-5.000 -0.3153 0.06032 0.05687 -0.0337 0.9994 0.0368
-4.750 -0.2850 0.05650 0.05301 -0.0376 0.9959 0.0383
-4.500 -0.2459 0.05256 0.04894 -0.0435 0.9917 0.0410
-4.250 -0.1845 0.04808 0.04386 -0.0532 0.9864 0.0457
-4.000 -0.1531 0.04374 0.03959 -0.0570 0.9824 0.0473
-3.750 -0.1164 0.04071 0.03645 -0.0609 0.9763 0.0504
-3.500 -0.0597 0.03798 0.03307 -0.0668 0.9721 0.0577
-3.250 -0.0291 0.03438 0.02959 -0.0697 0.9654 0.0606
-3.000 0.0261 0.03517 0.02966 -0.0735 0.9597 0.0701
-2.750 0.0630 0.02915 0.02381 -0.0784 0.9572 0.0738
-0.500 0.3912 0.01604 0.00881 -0.0900 0.8976 0.0814
-0.250 0.4196 0.01513 0.00769 -0.0889 0.8848 0.0713
0.000 0.4471 0.01464 0.00714 -0.0880 0.8710 0.0699
0.250 0.4739 0.01380 0.00628 -0.0872 0.8564 0.0709
0.500 0.5007 0.01333 0.00577 -0.0863 0.8402 0.0701
0.750 0.5270 0.01268 0.00512 -0.0854 0.8226 0.0699
1.000 0.5524 0.01218 0.00464 -0.0844 0.8003 0.0704
1.250 0.5780 0.01166 0.00412 -0.0835 0.7761 0.0723
1.500 0.6036 0.01140 0.00378 -0.0826 0.7461 0.0758
1.750 0.6291 0.01132 0.00355 -0.0816 0.7111 0.0833
2.000 0.6542 0.01130 0.00333 -0.0807 0.6751 0.0957
2.250 0.6810 0.00953 0.00328 -0.0802 0.6402 1.0000
2.500 0.7050 0.00990 0.00332 -0.0791 0.6037 1.0000
2.750 0.7288 0.01029 0.00344 -0.0782 0.5680 1.0000
3.000 0.7528 0.01064 0.00359 -0.0773 0.5346 1.0000
3.250 0.7772 0.01100 0.00375 -0.0766 0.5070 1.0000
3.500 0.8018 0.01133 0.00394 -0.0760 0.4824 1.0000
3.750 0.8261 0.01170 0.00413 -0.0753 0.4615 1.0000
4.000 0.8509 0.01202 0.00437 -0.0747 0.4415 1.0000
4.250 0.8757 0.01235 0.00461 -0.0742 0.4243 1.0000
4.500 0.9009 0.01269 0.00488 -0.0737 0.4111 1.0000
4.750 0.9259 0.01304 0.00517 -0.0733 0.3992 1.0000
5.000 0.9507 0.01338 0.00547 -0.0728 0.3857 1.0000
5.250 0.9752 0.01370 0.00576 -0.0722 0.3709 1.0000
5.500 1.0001 0.01399 0.00608 -0.0717 0.3582 1.0000
5.750 1.0248 0.01428 0.00642 -0.0712 0.3452 1.0000
6.000 1.0488 0.01457 0.00673 -0.0706 0.3289 1.0000
6.250 1.0725 0.01488 0.00704 -0.0699 0.3116 1.0000
6.500 1.0960 0.01511 0.00731 -0.0692 0.2844 1.0000
6.750 1.1183 0.01548 0.00759 -0.0683 0.2341 1.0000
7.000 1.1307 0.01716 0.00848 -0.0663 0.1143 1.0000
7.250 1.1460 0.01865 0.00963 -0.0646 0.0738 1.0000
7.500 1.1640 0.01973 0.01071 -0.0632 0.0659 1.0000
7.750 1.1832 0.02058 0.01168 -0.0618 0.0623 1.0000
8.000 1.2008 0.02156 0.01278 -0.0603 0.0591 1.0000
8.250 1.2147 0.02284 0.01410 -0.0584 0.0559 1.0000
8.500 1.2262 0.02439 0.01569 -0.0561 0.0534 1.0000
8.750 1.2425 0.02549 0.01689 -0.0544 0.0518 1.0000
9.000 1.2579 0.02670 0.01821 -0.0527 0.0494 1.0000
9.250 1.2725 0.02804 0.01960 -0.0509 0.0469 1.0000
9.500 1.2876 0.02980 0.02135 -0.0494 0.0450 1.0000
9.750 1.3082 0.03282 0.02438 -0.0487 0.0428 1.0000
10.000 1.3240 0.03386 0.02564 -0.0470 0.0412 1.0000
10.250 1.3412 0.03550 0.02748 -0.0456 0.0395 1.0000
10.500 1.3588 0.03749 0.02965 -0.0444 0.0381 1.0000
10.750 1.3752 0.03953 0.03181 -0.0432 0.0365 1.0000
11.000 1.3918 0.04221 0.03454 -0.0425 0.0347 1.0000
11.250 1.4054 0.04820 0.04083 -0.0420 0.0333 1.0000
11.500 1.4065 0.04986 0.04282 -0.0388 0.0329 1.0000
11.750 1.4055 0.05223 0.04552 -0.0358 0.0326 1.0000
12.000 1.3994 0.05485 0.04842 -0.0322 0.0324 1.0000
12.250 1.3901 0.05776 0.05161 -0.0289 0.0323 1.0000
12.500 1.3779 0.06082 0.05494 -0.0260 0.0322 1.0000
12.750 1.3638 0.06418 0.05856 -0.0237 0.0321 1.0000
13.000 1.3476 0.06792 0.06255 -0.0221 0.0320 1.0000
13.250 1.3297 0.07212 0.06698 -0.0213 0.0320 1.0000
13.500 1.3104 0.07684 0.07192 -0.0214 0.0320 1.0000
13.750 1.2897 0.08219 0.07749 -0.0225 0.0321 1.0000
14.000 1.2682 0.08820 0.08369 -0.0245 0.0323 1.0000
14.250 1.2460 0.09499 0.09065 -0.0273 0.0326 1.0000
14.750 1.1748 0.11531 0.11162 -0.0419 0.0365 1.0000
15.000 1.1822 0.11747 0.11374 -0.0414 0.0351 1.0000
15.250 1.0845 0.14814 0.14470 -0.0634 0.0420 1.0000
15.500 0.8515 0.13951 0.13628 -0.0431 0.0451 1.0000
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Polar data table (+)
Polar graphs
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