GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 735 AIRFOIL (goe735-il) Reynolds number: 200,000 Max Cl/Cd: 55.43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe735-il-200000-n5.txt Download as CSV file: xf-goe735-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 735 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 -0.7578 0.08302 0.07843 -0.0518 1.0000 0.0527
-16.500 -0.8029 0.07235 0.06758 -0.0590 1.0000 0.0531
-16.250 -0.8338 0.06418 0.05927 -0.0647 1.0000 0.0536
-16.000 -0.8555 0.05771 0.05267 -0.0692 1.0000 0.0541
-15.500 -0.8750 0.04788 0.04249 -0.0774 0.9115 0.0554
-15.250 -0.8742 0.04421 0.03852 -0.0809 0.8735 0.0564
-15.000 -0.8799 0.04126 0.03531 -0.0816 0.8509 0.0574
-14.750 -0.8845 0.03881 0.03260 -0.0814 0.8351 0.0583
-14.500 -0.8831 0.03719 0.03090 -0.0806 0.8220 0.0590
-14.250 -0.8812 0.03579 0.02940 -0.0794 0.8103 0.0599
-14.000 -0.8790 0.03454 0.02803 -0.0778 0.8002 0.0609
-13.750 -0.8760 0.03334 0.02669 -0.0760 0.7907 0.0621
-13.500 -0.8723 0.03215 0.02531 -0.0740 0.7823 0.0635
-13.250 -0.8666 0.03109 0.02411 -0.0721 0.7734 0.0648
-13.000 -0.8587 0.03036 0.02331 -0.0700 0.7659 0.0658
-12.750 -0.8495 0.02964 0.02252 -0.0679 0.7580 0.0671
-12.500 -0.8400 0.02891 0.02168 -0.0658 0.7501 0.0686
-12.250 -0.8299 0.02814 0.02072 -0.0636 0.7434 0.0703
-12.000 -0.8182 0.02745 0.01995 -0.0615 0.7354 0.0717
-11.750 -0.8060 0.02697 0.01941 -0.0593 0.7282 0.0731
-11.500 -0.7931 0.02649 0.01885 -0.0571 0.7214 0.0747
-11.250 -0.7791 0.02595 0.01820 -0.0550 0.7137 0.0766
-11.000 -0.7650 0.02541 0.01747 -0.0528 0.7067 0.0786
-10.750 -0.7503 0.02504 0.01708 -0.0507 0.6995 0.0799
-10.500 -0.7337 0.02468 0.01667 -0.0489 0.6916 0.0815
-10.250 -0.7158 0.02427 0.01615 -0.0472 0.6845 0.0835
-10.000 -0.6964 0.02382 0.01555 -0.0458 0.6771 0.0856
-9.750 -0.6768 0.02338 0.01505 -0.0445 0.6690 0.0874
-9.500 -0.6572 0.02306 0.01466 -0.0430 0.6618 0.0891
-9.250 -0.6361 0.02270 0.01427 -0.0418 0.6529 0.0912
-9.000 -0.6147 0.02234 0.01377 -0.0406 0.6450 0.0934
-8.750 -0.5925 0.02195 0.01324 -0.0395 0.6372 0.0956
-8.500 -0.5706 0.02158 0.01287 -0.0385 0.6284 0.0974
-8.250 -0.5485 0.02131 0.01253 -0.0374 0.6205 0.0996
-8.000 -0.5253 0.02101 0.01216 -0.0365 0.6112 0.1021
-7.750 -0.5020 0.02073 0.01171 -0.0355 0.6033 0.1046
-7.500 -0.4784 0.02034 0.01132 -0.0347 0.5949 0.1067
-7.250 -0.4549 0.02005 0.01098 -0.0338 0.5864 0.1088
-7.000 -0.4309 0.01978 0.01065 -0.0330 0.5783 0.1112
-6.750 -0.4064 0.01950 0.01028 -0.0323 0.5699 0.1135
-6.500 -0.3818 0.01926 0.00988 -0.0315 0.5628 0.1158
-6.250 -0.3574 0.01889 0.00954 -0.0308 0.5551 0.1180
-6.000 -0.3331 0.01863 0.00924 -0.0301 0.5477 0.1202
-5.750 -0.3084 0.01841 0.00895 -0.0294 0.5409 0.1226
-5.500 -0.2833 0.01818 0.00866 -0.0287 0.5336 0.1253
-5.250 -0.2582 0.01800 0.00837 -0.0281 0.5270 0.1280
-5.000 -0.2340 0.01772 0.00809 -0.0273 0.5214 0.1307
-4.750 -0.2093 0.01750 0.00787 -0.0266 0.5149 0.1334
-4.500 -0.1845 0.01733 0.00764 -0.0260 0.5088 0.1366
-4.250 -0.1594 0.01720 0.00742 -0.0253 0.5033 0.1401
-4.000 -0.1347 0.01699 0.00723 -0.0246 0.4974 0.1436
-3.750 -0.1102 0.01681 0.00705 -0.0239 0.4920 0.1474
-3.500 -0.0855 0.01669 0.00686 -0.0232 0.4872 0.1517
-3.250 -0.0602 0.01659 0.00671 -0.0226 0.4824 0.1563
-3.000 -0.0361 0.01640 0.00658 -0.0218 0.4770 0.1617
-2.750 -0.0113 0.01628 0.00645 -0.0211 0.4719 0.1681
-2.500 0.0131 0.01619 0.00631 -0.0204 0.4673 0.1747
-2.250 0.0375 0.01607 0.00621 -0.0197 0.4631 0.1832
-2.000 0.0622 0.01595 0.00614 -0.0190 0.4586 0.1935
-1.500 0.1105 0.01574 0.00600 -0.0175 0.4500 0.2249
-1.000 0.1572 0.01547 0.00593 -0.0158 0.4418 0.2800
-0.750 0.1798 0.01531 0.00593 -0.0148 0.4376 0.3181
-0.500 0.2019 0.01516 0.00591 -0.0137 0.4337 0.3600
-0.250 0.2229 0.01498 0.00588 -0.0124 0.4303 0.4091
0.250 0.2575 0.01437 0.00594 -0.0082 0.4239 0.5802
0.500 0.2777 0.01405 0.00607 -0.0064 0.4200 0.6807
0.750 0.3214 0.01402 0.00639 -0.0091 0.4155 0.7906
1.000 0.3793 0.01429 0.00668 -0.0146 0.4111 0.8425
1.250 0.4259 0.01459 0.00693 -0.0181 0.4075 0.8696
1.500 0.4664 0.01486 0.00720 -0.0203 0.4037 0.8870
1.750 0.5021 0.01514 0.00746 -0.0217 0.4000 0.9020
2.000 0.5385 0.01551 0.00778 -0.0230 0.3964 0.9191
2.250 0.5773 0.01592 0.00810 -0.0248 0.3929 0.9345
2.500 0.6186 0.01628 0.00836 -0.0272 0.3896 0.9440
2.750 0.6532 0.01652 0.00861 -0.0286 0.3860 0.9512
3.000 0.6931 0.01676 0.00883 -0.0311 0.3825 0.9573
3.250 0.7264 0.01702 0.00906 -0.0323 0.3793 0.9652
3.500 0.7665 0.01722 0.00919 -0.0349 0.3763 0.9695
3.750 0.7990 0.01743 0.00931 -0.0361 0.3736 0.9740
4.000 0.8269 0.01766 0.00952 -0.0364 0.3708 0.9787
4.250 0.8624 0.01782 0.00971 -0.0383 0.3674 0.9816
4.500 0.8980 0.01800 0.00990 -0.0402 0.3640 0.9856
4.750 0.9318 0.01822 0.01009 -0.0418 0.3612 0.9900
5.000 0.9654 0.01840 0.01024 -0.0434 0.3585 0.9934
5.250 0.9978 0.01859 0.01037 -0.0447 0.3562 0.9962
5.500 1.0294 0.01882 0.01057 -0.0460 0.3537 0.9989
5.750 1.0529 0.01906 0.01088 -0.0457 0.3509 1.0000
6.000 1.0693 0.01933 0.01118 -0.0441 0.3481 1.0000
6.250 1.0855 0.01960 0.01146 -0.0424 0.3456 1.0000
6.500 1.1013 0.01987 0.01175 -0.0407 0.3433 1.0000
6.750 1.1170 0.02016 0.01201 -0.0389 0.3412 1.0000
7.000 1.1329 0.02045 0.01226 -0.0372 0.3391 1.0000
7.250 1.1480 0.02077 0.01256 -0.0353 0.3369 1.0000
7.500 1.1590 0.02115 0.01302 -0.0329 0.3345 1.0000
7.750 1.1693 0.02154 0.01346 -0.0304 0.3321 1.0000
8.000 1.1788 0.02193 0.01388 -0.0277 0.3297 1.0000
8.250 1.1872 0.02231 0.01429 -0.0249 0.3273 1.0000
8.500 1.1926 0.02267 0.01465 -0.0216 0.3251 1.0000
8.750 1.1975 0.02301 0.01497 -0.0182 0.3230 1.0000
9.000 1.2074 0.02338 0.01529 -0.0156 0.3211 1.0000
9.250 1.2080 0.02396 0.01594 -0.0121 0.3189 1.0000
9.500 1.2084 0.02467 0.01674 -0.0089 0.3165 1.0000
9.750 1.2114 0.02542 0.01755 -0.0062 0.3139 1.0000
10.000 1.2168 0.02618 0.01835 -0.0039 0.3114 1.0000
10.250 1.2241 0.02692 0.01911 -0.0020 0.3090 1.0000
10.500 1.2350 0.02756 0.01974 -0.0005 0.3067 1.0000
10.750 1.2500 0.02809 0.02023 0.0007 0.3048 1.0000
11.000 1.2554 0.02912 0.02132 0.0024 0.3026 1.0000
11.250 1.2556 0.03049 0.02281 0.0042 0.3000 1.0000
11.500 1.2579 0.03183 0.02424 0.0057 0.2973 1.0000
11.750 1.2619 0.03313 0.02559 0.0070 0.2946 1.0000
12.000 1.2692 0.03425 0.02674 0.0081 0.2920 1.0000
12.250 1.2821 0.03503 0.02751 0.0089 0.2899 1.0000
12.500 1.2991 0.03558 0.02802 0.0096 0.2878 1.0000
12.750 1.2877 0.03821 0.03083 0.0109 0.2849 1.0000
13.000 1.2808 0.04067 0.03342 0.0119 0.2818 1.0000
13.250 1.2782 0.04286 0.03569 0.0127 0.2789 1.0000
13.500 1.2819 0.04458 0.03745 0.0132 0.2762 1.0000
13.750 1.2961 0.04540 0.03825 0.0136 0.2741 1.0000
14.000 1.3077 0.04646 0.03932 0.0141 0.2716 1.0000
14.250 1.2682 0.05265 0.04576 0.0142 0.2668 1.0000
14.500 1.2532 0.05667 0.04989 0.0141 0.2628 1.0000
14.750 1.2591 0.05850 0.05174 0.0142 0.2601 1.0000
15.000 1.2786 0.05882 0.05204 0.0145 0.2583 1.0000
15.250 1.1907 0.07176 0.06529 0.0126 0.2497 1.0000
15.500 1.1866 0.07501 0.06858 0.0122 0.2461 1.0000
15.750 1.2065 0.07526 0.06883 0.0124 0.2443 1.0000
16.000 1.2343 0.07454 0.06808 0.0128 0.2430 1.0000
16.500 1.1056 0.09725 0.09111 0.0080 0.2256 1.0000
16.750 1.1499 0.09408 0.08791 0.0089 0.2267 1.0000
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Polar data table (+)
Polar graphs
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