GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 702 AIRFOIL (goe702-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.21 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe702-il-1000000-n5.txt Download as CSV file: xf-goe702-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 702 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.7948 0.08729 0.08411 -0.0644 0.8709 0.0309
-17.250 -0.8182 0.08056 0.07725 -0.0687 0.8581 0.0310
-17.000 -0.8493 0.07307 0.06963 -0.0734 0.8464 0.0312
-16.750 -0.8909 0.06490 0.06130 -0.0784 0.8337 0.0313
-16.500 -0.9526 0.05498 0.05119 -0.0845 0.8198 0.0312
-16.250 -1.1248 0.03093 0.02661 -0.1023 0.7969 0.0307
-16.000 -1.1422 0.02815 0.02365 -0.1012 0.7793 0.0309
-15.750 -1.1495 0.02658 0.02193 -0.0984 0.7650 0.0310
-15.500 -1.1511 0.02548 0.02070 -0.0953 0.7521 0.0312
-15.250 -1.1453 0.02455 0.01967 -0.0929 0.7421 0.0314
-15.000 -1.1337 0.02372 0.01873 -0.0912 0.7326 0.0316
-14.750 -1.1196 0.02294 0.01786 -0.0897 0.7251 0.0318
-14.500 -1.1037 0.02223 0.01705 -0.0883 0.7171 0.0320
-14.250 -1.0863 0.02159 0.01631 -0.0870 0.7100 0.0322
-14.000 -1.0675 0.02097 0.01561 -0.0858 0.7040 0.0324
-13.750 -1.0488 0.02032 0.01488 -0.0847 0.6979 0.0327
-13.500 -1.0298 0.01966 0.01415 -0.0835 0.6924 0.0330
-13.250 -1.0092 0.01907 0.01350 -0.0825 0.6879 0.0333
-13.000 -0.9875 0.01854 0.01292 -0.0816 0.6836 0.0337
-12.750 -0.9652 0.01805 0.01237 -0.0808 0.6791 0.0341
-12.500 -0.9421 0.01761 0.01187 -0.0800 0.6743 0.0345
-12.250 -0.9186 0.01720 0.01140 -0.0792 0.6691 0.0350
-12.000 -0.8945 0.01680 0.01094 -0.0785 0.6646 0.0354
-11.750 -0.8702 0.01641 0.01050 -0.0778 0.6592 0.0358
-11.500 -0.8456 0.01606 0.01007 -0.0771 0.6538 0.0361
-11.250 -0.8207 0.01572 0.00967 -0.0765 0.6487 0.0364
-11.000 -0.7959 0.01532 0.00922 -0.0758 0.6446 0.0369
-10.750 -0.7708 0.01493 0.00880 -0.0752 0.6407 0.0374
-10.500 -0.7453 0.01459 0.00842 -0.0746 0.6368 0.0380
-10.250 -0.7196 0.01429 0.00807 -0.0741 0.6321 0.0385
-10.000 -0.6934 0.01400 0.00774 -0.0736 0.6276 0.0391
-9.750 -0.6670 0.01372 0.00742 -0.0731 0.6232 0.0397
-9.500 -0.6403 0.01346 0.00711 -0.0726 0.6187 0.0403
-9.250 -0.6135 0.01324 0.00683 -0.0722 0.6142 0.0409
-9.000 -0.5871 0.01295 0.00651 -0.0717 0.6101 0.0417
-8.750 -0.5602 0.01268 0.00622 -0.0713 0.6068 0.0426
-8.500 -0.5330 0.01244 0.00596 -0.0709 0.6030 0.0434
-8.250 -0.5057 0.01222 0.00571 -0.0705 0.5991 0.0443
-8.000 -0.4782 0.01203 0.00547 -0.0702 0.5952 0.0452
-7.750 -0.4507 0.01185 0.00525 -0.0698 0.5909 0.0459
-7.500 -0.4233 0.01161 0.00500 -0.0695 0.5873 0.0470
-7.250 -0.3956 0.01140 0.00478 -0.0692 0.5826 0.0481
-7.000 -0.3678 0.01122 0.00457 -0.0688 0.5775 0.0493
-6.750 -0.3400 0.01107 0.00438 -0.0685 0.5727 0.0504
-6.500 -0.3120 0.01090 0.00418 -0.0683 0.5683 0.0516
-6.250 -0.2841 0.01071 0.00399 -0.0680 0.5626 0.0533
-6.000 -0.2562 0.01057 0.00381 -0.0677 0.5552 0.0550
-5.750 -0.2280 0.01044 0.00365 -0.0674 0.5487 0.0564
-5.500 -0.2000 0.01029 0.00348 -0.0672 0.5408 0.0582
-5.250 -0.1721 0.01017 0.00333 -0.0669 0.5326 0.0604
-5.000 -0.1439 0.01006 0.00319 -0.0667 0.5222 0.0625
-4.750 -0.1161 0.00996 0.00306 -0.0664 0.5092 0.0656
-4.500 -0.0884 0.00991 0.00294 -0.0661 0.4919 0.0690
-4.250 -0.0609 0.00987 0.00285 -0.0658 0.4737 0.0732
-4.000 -0.0333 0.00985 0.00278 -0.0655 0.4585 0.0773
-3.750 -0.0055 0.00983 0.00273 -0.0652 0.4457 0.0820
-3.500 0.0225 0.00981 0.00267 -0.0650 0.4361 0.0861
-3.000 0.0787 0.00979 0.00259 -0.0645 0.4191 0.0935
-2.750 0.1067 0.00977 0.00255 -0.0643 0.4117 0.0970
-2.500 0.1348 0.00976 0.00253 -0.0641 0.4057 0.1004
-2.250 0.1633 0.00974 0.00249 -0.0640 0.4015 0.1029
-2.000 0.1916 0.00972 0.00246 -0.0638 0.3971 0.1055
-1.750 0.2197 0.00970 0.00243 -0.0636 0.3923 0.1089
-1.500 0.2478 0.00971 0.00242 -0.0634 0.3874 0.1117
-1.250 0.2763 0.00969 0.00240 -0.0633 0.3841 0.1144
-1.000 0.3046 0.00968 0.00238 -0.0631 0.3801 0.1177
-0.750 0.3327 0.00966 0.00237 -0.0629 0.3762 0.1216
-0.500 0.3607 0.00968 0.00238 -0.0627 0.3724 0.1258
-0.250 0.3886 0.00969 0.00239 -0.0625 0.3687 0.1310
0.000 0.4168 0.00965 0.00239 -0.0624 0.3665 0.1398
0.250 0.4448 0.00961 0.00239 -0.0622 0.3635 0.1513
0.500 0.4726 0.00959 0.00240 -0.0620 0.3599 0.1646
0.750 0.5000 0.00957 0.00243 -0.0618 0.3563 0.1844
1.000 0.5272 0.00956 0.00248 -0.0615 0.3525 0.2082
1.250 0.5548 0.00955 0.00253 -0.0613 0.3499 0.2287
1.500 0.5828 0.00956 0.00258 -0.0612 0.3478 0.2446
1.750 0.6106 0.00957 0.00263 -0.0610 0.3453 0.2585
2.000 0.6383 0.00960 0.00269 -0.0608 0.3426 0.2701
2.250 0.6659 0.00967 0.00276 -0.0606 0.3395 0.2802
2.500 0.6930 0.00973 0.00284 -0.0604 0.3362 0.2922
2.750 0.7203 0.00982 0.00293 -0.0602 0.3328 0.3010
3.000 0.7479 0.00985 0.00300 -0.0600 0.3308 0.3111
3.250 0.7754 0.00990 0.00308 -0.0598 0.3287 0.3200
3.500 0.8027 0.00996 0.00316 -0.0596 0.3263 0.3305
3.750 0.8296 0.01002 0.00326 -0.0593 0.3237 0.3454
4.000 0.8561 0.01009 0.00337 -0.0590 0.3210 0.3663
4.250 0.8823 0.01016 0.00349 -0.0587 0.3182 0.3875
4.500 0.9083 0.01023 0.00362 -0.0583 0.3155 0.4116
5.000 0.9602 0.01024 0.00386 -0.0575 0.3114 0.4938
5.500 1.0485 0.00955 0.00432 -0.0645 0.3060 0.9808
5.750 1.0839 0.00974 0.00448 -0.0662 0.3032 0.9890
6.000 1.1153 0.00995 0.00466 -0.0670 0.3001 0.9957
6.250 1.1507 0.01011 0.00482 -0.0687 0.2980 0.9990
6.500 1.1807 0.01025 0.00497 -0.0692 0.2960 1.0000
6.750 1.2039 0.01040 0.00512 -0.0683 0.2941 1.0000
7.000 1.2268 0.01057 0.00528 -0.0674 0.2919 1.0000
7.250 1.2492 0.01075 0.00546 -0.0665 0.2896 1.0000
7.500 1.2711 0.01095 0.00565 -0.0654 0.2870 1.0000
7.750 1.2924 0.01118 0.00587 -0.0643 0.2842 1.0000
8.000 1.3144 0.01138 0.00607 -0.0633 0.2823 1.0000
8.250 1.3368 0.01155 0.00626 -0.0624 0.2808 1.0000
8.500 1.3586 0.01173 0.00646 -0.0614 0.2787 1.0000
8.750 1.3797 0.01194 0.00668 -0.0603 0.2762 1.0000
9.000 1.3990 0.01221 0.00694 -0.0590 0.2722 1.0000
9.250 1.4158 0.01256 0.00725 -0.0573 0.2675 1.0000
9.500 1.4344 0.01278 0.00750 -0.0558 0.2645 1.0000
9.750 1.4493 0.01304 0.00778 -0.0537 0.2616 1.0000
10.000 1.4636 0.01336 0.00811 -0.0516 0.2589 1.0000
10.250 1.4769 0.01379 0.00854 -0.0496 0.2554 1.0000
10.500 1.4904 0.01431 0.00906 -0.0479 0.2524 1.0000
10.750 1.5076 0.01474 0.00953 -0.0468 0.2502 1.0000
11.000 1.5246 0.01523 0.01004 -0.0458 0.2470 1.0000
11.250 1.5404 0.01581 0.01064 -0.0447 0.2434 1.0000
11.500 1.5547 0.01652 0.01135 -0.0436 0.2396 1.0000
11.750 1.5694 0.01725 0.01209 -0.0427 0.2358 1.0000
12.000 1.5857 0.01790 0.01277 -0.0419 0.2324 1.0000
12.250 1.6000 0.01870 0.01358 -0.0410 0.2281 1.0000
12.500 1.6103 0.01981 0.01468 -0.0400 0.2222 1.0000
12.750 1.6248 0.02065 0.01555 -0.0392 0.2183 1.0000
13.000 1.6366 0.02171 0.01663 -0.0384 0.2130 1.0000
13.250 1.6451 0.02304 0.01795 -0.0375 0.2072 1.0000
13.500 1.6554 0.02426 0.01918 -0.0367 0.2013 1.0000
13.750 1.6607 0.02588 0.02080 -0.0358 0.1950 1.0000
14.000 1.6689 0.02730 0.02223 -0.0350 0.1893 1.0000
14.250 1.6709 0.02921 0.02414 -0.0341 0.1820 1.0000
14.500 1.6695 0.03146 0.02637 -0.0331 0.1718 1.0000
14.750 1.6648 0.03401 0.02891 -0.0321 0.1622 1.0000
15.000 1.6578 0.03692 0.03179 -0.0312 0.1527 1.0000
15.250 1.6485 0.04012 0.03498 -0.0304 0.1431 1.0000
15.500 1.6372 0.04364 0.03849 -0.0298 0.1327 1.0000
15.750 1.6226 0.04762 0.04246 -0.0293 0.1222 1.0000
16.000 1.6044 0.05213 0.04696 -0.0291 0.1116 1.0000
16.250 1.5898 0.05640 0.05126 -0.0290 0.1041 1.0000
16.500 1.5720 0.06119 0.05608 -0.0291 0.0972 1.0000
17.000 1.5356 0.07125 0.06622 -0.0300 0.0854 1.0000
17.250 1.5213 0.07598 0.07100 -0.0305 0.0820 1.0000
17.500 1.5088 0.08051 0.07560 -0.0311 0.0792 1.0000
17.750 1.4978 0.08488 0.08002 -0.0318 0.0765 1.0000
18.000 1.4870 0.08931 0.08450 -0.0325 0.0745 1.0000
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