GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 409 AIRFOIL (goe409-il) Reynolds number: 200,000 Max Cl/Cd: 37.7 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe409-il-200000-n5.txt Download as CSV file: xf-goe409-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 409 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8613 0.11213 0.10813 -0.0227 1.0000 0.0267
-16.500 -0.9195 0.09538 0.09121 -0.0329 1.0000 0.0257
-16.250 -0.9685 0.08211 0.07769 -0.0411 1.0000 0.0253
-16.000 -0.9993 0.07336 0.06871 -0.0462 1.0000 0.0253
-15.750 -1.0227 0.06649 0.06160 -0.0498 1.0000 0.0258
-15.500 -1.0428 0.06054 0.05539 -0.0523 1.0000 0.0264
-15.250 -1.0472 0.05717 0.05191 -0.0537 1.0000 0.0272
-15.000 -1.0476 0.05455 0.04920 -0.0546 1.0000 0.0278
-14.750 -1.0466 0.05231 0.04687 -0.0553 1.0000 0.0287
-14.500 -1.0505 0.04952 0.04392 -0.0555 1.0000 0.0297
-14.250 -1.0578 0.04642 0.04053 -0.0554 1.0000 0.0315
-14.000 -1.0612 0.04394 0.03783 -0.0548 1.0000 0.0325
-13.750 -1.0569 0.04272 0.03656 -0.0541 1.0000 0.0332
-13.500 -1.0531 0.04152 0.03529 -0.0531 1.0000 0.0341
-13.250 -1.0501 0.04033 0.03399 -0.0518 1.0000 0.0352
-13.000 -1.0484 0.03891 0.03240 -0.0501 1.0000 0.0365
-12.750 -1.0488 0.03749 0.03070 -0.0479 1.0000 0.0381
-12.500 -1.0473 0.03620 0.02918 -0.0456 1.0000 0.0391
-12.250 -1.0392 0.03538 0.02837 -0.0438 1.0000 0.0400
-12.000 -1.0317 0.03464 0.02760 -0.0416 1.0000 0.0409
-11.750 -1.0254 0.03400 0.02689 -0.0391 1.0000 0.0420
-11.500 -1.0202 0.03330 0.02608 -0.0363 1.0000 0.0432
-11.250 -1.0155 0.03264 0.02529 -0.0330 1.0000 0.0444
-11.000 -1.0090 0.03193 0.02442 -0.0300 1.0000 0.0456
-10.750 -1.0019 0.03141 0.02372 -0.0269 1.0000 0.0467
-10.500 -0.9946 0.03091 0.02307 -0.0238 1.0000 0.0475
-10.250 -0.9790 0.02942 0.02157 -0.0225 1.0000 0.0491
-10.000 -0.9674 0.02876 0.02092 -0.0202 1.0000 0.0506
-9.750 -0.9566 0.02820 0.02031 -0.0177 1.0000 0.0521
-9.500 -0.9454 0.02761 0.01964 -0.0151 1.0000 0.0535
-9.250 -0.9322 0.02688 0.01882 -0.0128 1.0000 0.0544
-9.000 -0.9181 0.02612 0.01796 -0.0105 1.0000 0.0550
-8.750 -0.9037 0.02539 0.01713 -0.0084 1.0000 0.0556
-8.500 -0.8893 0.02476 0.01641 -0.0061 1.0000 0.0563
-8.250 -0.8749 0.02417 0.01574 -0.0039 1.0000 0.0569
-8.000 -0.8601 0.02361 0.01510 -0.0017 1.0000 0.0575
-7.750 -0.8449 0.02303 0.01446 0.0004 1.0000 0.0578
-7.500 -0.8297 0.02247 0.01383 0.0025 1.0000 0.0582
-7.250 -0.8130 0.02183 0.01316 0.0043 0.9997 0.0586
-7.000 -0.7846 0.02087 0.01220 0.0036 0.9971 0.0594
-6.750 -0.7562 0.02006 0.01139 0.0028 0.9941 0.0603
-6.500 -0.7286 0.01938 0.01069 0.0023 0.9907 0.0612
-6.250 -0.6991 0.01876 0.01006 0.0014 0.9869 0.0622
-6.000 -0.6659 0.01820 0.00948 -0.0002 0.9837 0.0634
-5.750 -0.6367 0.01769 0.00893 -0.0009 0.9785 0.0649
-5.500 -0.6031 0.01722 0.00842 -0.0024 0.9743 0.0665
-5.250 -0.5690 0.01678 0.00794 -0.0040 0.9704 0.0680
-5.000 -0.5385 0.01639 0.00749 -0.0048 0.9647 0.0693
-4.750 -0.5025 0.01601 0.00706 -0.0067 0.9611 0.0708
-4.500 -0.4702 0.01561 0.00665 -0.0078 0.9571 0.0733
-4.250 -0.4425 0.01525 0.00628 -0.0080 0.9516 0.0766
-4.000 -0.4100 0.01488 0.00593 -0.0092 0.9480 0.0820
-3.750 -0.3824 0.01417 0.00557 -0.0096 0.9439 0.1353
-3.500 -0.3598 0.01374 0.00532 -0.0088 0.9366 0.1775
-3.250 -0.3310 0.01318 0.00502 -0.0093 0.9321 0.2300
-3.000 -0.3099 0.01266 0.00478 -0.0082 0.9245 0.2885
-2.750 -0.2868 0.01205 0.00456 -0.0075 0.9179 0.3715
-2.500 -0.2645 0.01166 0.00444 -0.0064 0.9107 0.4381
-2.250 -0.2394 0.01140 0.00432 -0.0058 0.9033 0.4781
-2.000 -0.2143 0.01113 0.00419 -0.0051 0.8958 0.5166
-1.750 -0.1898 0.01087 0.00407 -0.0043 0.8874 0.5498
-1.500 -0.1649 0.01063 0.00398 -0.0035 0.8790 0.5799
-1.250 -0.1393 0.01037 0.00390 -0.0027 0.8706 0.6183
-1.000 -0.1154 0.01014 0.00389 -0.0016 0.8602 0.6633
-0.750 -0.0880 0.00993 0.00386 -0.0010 0.8502 0.7089
-0.500 -0.0592 0.00979 0.00389 -0.0005 0.8378 0.7497
-0.250 -0.0300 0.00973 0.00393 -0.0002 0.8230 0.7820
0.000 0.0001 0.00971 0.00392 0.0000 0.8056 0.8058
0.250 0.0299 0.00973 0.00392 0.0002 0.7814 0.8229
0.500 0.0592 0.00979 0.00388 0.0006 0.7485 0.8379
0.750 0.0879 0.00993 0.00386 0.0010 0.7087 0.8502
1.000 0.1154 0.01014 0.00389 0.0016 0.6628 0.8603
1.250 0.1393 0.01037 0.00390 0.0028 0.6182 0.8707
1.500 0.1648 0.01063 0.00398 0.0035 0.5796 0.8790
1.750 0.1897 0.01087 0.00407 0.0043 0.5495 0.8874
2.250 0.2393 0.01141 0.00432 0.0058 0.4777 0.9033
2.500 0.2645 0.01166 0.00444 0.0064 0.4380 0.9107
2.750 0.2865 0.01206 0.00456 0.0075 0.3682 0.9180
3.000 0.3097 0.01267 0.00478 0.0082 0.2860 0.9245
3.250 0.3308 0.01319 0.00503 0.0093 0.2277 0.9321
3.500 0.3595 0.01376 0.00533 0.0088 0.1753 0.9367
3.750 0.3822 0.01418 0.00557 0.0097 0.1334 0.9440
4.000 0.4100 0.01487 0.00592 0.0092 0.0822 0.9480
4.250 0.4426 0.01525 0.00628 0.0080 0.0767 0.9516
4.500 0.4702 0.01561 0.00664 0.0078 0.0733 0.9571
4.750 0.5025 0.01601 0.00706 0.0067 0.0708 0.9611
5.000 0.5385 0.01639 0.00749 0.0048 0.0693 0.9647
5.250 0.5690 0.01678 0.00794 0.0040 0.0680 0.9705
5.500 0.6031 0.01722 0.00842 0.0024 0.0666 0.9744
5.750 0.6367 0.01769 0.00893 0.0009 0.0649 0.9785
6.000 0.6659 0.01820 0.00947 0.0002 0.0635 0.9837
6.250 0.6991 0.01876 0.01006 -0.0014 0.0622 0.9869
6.500 0.7286 0.01938 0.01069 -0.0023 0.0612 0.9907
6.750 0.7563 0.02006 0.01139 -0.0028 0.0603 0.9942
7.000 0.7848 0.02087 0.01220 -0.0036 0.0594 0.9971
7.250 0.8131 0.02185 0.01318 -0.0043 0.0585 0.9998
7.500 0.8296 0.02247 0.01383 -0.0025 0.0581 1.0000
7.750 0.8449 0.02303 0.01446 -0.0004 0.0579 1.0000
8.000 0.8600 0.02359 0.01509 0.0018 0.0575 1.0000
8.250 0.8747 0.02415 0.01572 0.0039 0.0569 1.0000
8.500 0.8893 0.02475 0.01640 0.0062 0.0563 1.0000
8.750 0.9037 0.02540 0.01714 0.0084 0.0556 1.0000
9.000 0.9181 0.02612 0.01796 0.0106 0.0550 1.0000
9.250 0.9322 0.02688 0.01882 0.0128 0.0544 1.0000
9.500 0.9452 0.02759 0.01962 0.0151 0.0534 1.0000
9.750 0.9565 0.02819 0.02030 0.0177 0.0521 1.0000
10.000 0.9673 0.02874 0.02089 0.0203 0.0506 1.0000
10.250 0.9791 0.02941 0.02156 0.0225 0.0491 1.0000
10.500 0.9949 0.03096 0.02312 0.0237 0.0474 1.0000
10.750 1.0018 0.03136 0.02368 0.0270 0.0466 1.0000
11.000 1.0092 0.03193 0.02442 0.0300 0.0456 1.0000
11.250 1.0157 0.03261 0.02526 0.0330 0.0444 1.0000
11.500 1.0204 0.03328 0.02605 0.0362 0.0431 1.0000
11.750 1.0257 0.03396 0.02683 0.0391 0.0420 1.0000
12.000 1.0323 0.03464 0.02759 0.0415 0.0409 1.0000
12.250 1.0398 0.03539 0.02838 0.0437 0.0400 1.0000
12.500 1.0480 0.03620 0.02918 0.0455 0.0391 1.0000
12.750 1.0490 0.03748 0.03071 0.0479 0.0380 1.0000
13.000 1.0491 0.03888 0.03236 0.0500 0.0364 1.0000
13.250 1.0511 0.04023 0.03388 0.0517 0.0351 1.0000
13.500 1.0542 0.04146 0.03523 0.0530 0.0340 1.0000
13.750 1.0581 0.04266 0.03650 0.0539 0.0332 1.0000
14.000 1.0624 0.04392 0.03782 0.0546 0.0325 1.0000
14.250 1.0581 0.04651 0.04065 0.0552 0.0312 1.0000
14.500 1.0514 0.04956 0.04397 0.0554 0.0298 1.0000
14.750 1.0486 0.05218 0.04674 0.0551 0.0286 1.0000
15.000 1.0462 0.05493 0.04961 0.0544 0.0279 1.0000
15.250 1.0503 0.05691 0.05163 0.0535 0.0271 1.0000
15.500 1.0464 0.06019 0.05501 0.0522 0.0266 1.0000
15.750 1.0246 0.06641 0.06152 0.0496 0.0259 1.0000
16.000 1.0000 0.07350 0.06886 0.0459 0.0253 1.0000
16.250 0.9694 0.08225 0.07784 0.0408 0.0251 1.0000
16.500 0.9246 0.09465 0.09047 0.0331 0.0257 1.0000
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Polar data table (+)
Polar graphs
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