GOE 741 AIRFOIL (goe741-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 741 AIRFOIL (goe741-il) Reynolds number: 500,000 Max Cl/Cd: 92.99 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe741-il-500000-n5.txt Download as CSV file: xf-goe741-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 741 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8642 0.04386 0.03952 -0.0479 0.6340 0.0257
-12.500 -0.8887 0.04013 0.03553 -0.0456 0.6284 0.0257
-12.250 -0.9011 0.03773 0.03294 -0.0423 0.6218 0.0258
-12.000 -0.9062 0.03578 0.03078 -0.0392 0.6150 0.0260
-11.750 -0.9034 0.03392 0.02871 -0.0369 0.6086 0.0261
-11.500 -0.8963 0.03225 0.02684 -0.0348 0.6019 0.0263
-11.250 -0.8864 0.03071 0.02509 -0.0329 0.5950 0.0264
-11.000 -0.8741 0.02929 0.02346 -0.0311 0.5889 0.0266
-10.750 -0.8594 0.02803 0.02201 -0.0295 0.5824 0.0267
-10.500 -0.8431 0.02686 0.02065 -0.0280 0.5758 0.0269
-10.250 -0.8253 0.02581 0.01941 -0.0267 0.5700 0.0271
-10.000 -0.8062 0.02482 0.01826 -0.0254 0.5646 0.0272
-9.750 -0.7861 0.02393 0.01720 -0.0242 0.5593 0.0273
-9.500 -0.7650 0.02313 0.01624 -0.0232 0.5545 0.0275
-9.250 -0.7430 0.02240 0.01536 -0.0222 0.5504 0.0276
-9.000 -0.7207 0.02165 0.01449 -0.0212 0.5462 0.0278
-8.750 -0.6988 0.02080 0.01355 -0.0202 0.5417 0.0280
-8.500 -0.6757 0.02014 0.01280 -0.0193 0.5373 0.0282
-8.250 -0.6519 0.01958 0.01216 -0.0185 0.5333 0.0284
-8.000 -0.6274 0.01904 0.01157 -0.0178 0.5302 0.0286
-7.750 -0.6026 0.01855 0.01101 -0.0171 0.5270 0.0289
-7.500 -0.5774 0.01809 0.01049 -0.0165 0.5236 0.0292
-7.250 -0.5520 0.01764 0.00997 -0.0158 0.5202 0.0294
-7.000 -0.5265 0.01722 0.00948 -0.0152 0.5168 0.0297
-6.750 -0.5007 0.01683 0.00900 -0.0147 0.5136 0.0300
-6.500 -0.4744 0.01644 0.00857 -0.0141 0.5109 0.0305
-6.250 -0.4480 0.01608 0.00815 -0.0136 0.5083 0.0309
-6.000 -0.4215 0.01574 0.00774 -0.0131 0.5055 0.0313
-5.750 -0.3948 0.01542 0.00736 -0.0127 0.5027 0.0316
-5.500 -0.3686 0.01504 0.00693 -0.0122 0.4998 0.0319
-5.250 -0.3422 0.01469 0.00655 -0.0117 0.4969 0.0324
-5.000 -0.3154 0.01440 0.00623 -0.0113 0.4942 0.0328
-4.750 -0.2882 0.01413 0.00595 -0.0109 0.4921 0.0333
-4.500 -0.2609 0.01387 0.00568 -0.0105 0.4898 0.0339
-4.250 -0.2335 0.01363 0.00542 -0.0102 0.4873 0.0345
-4.000 -0.2061 0.01341 0.00516 -0.0098 0.4846 0.0351
-3.750 -0.1786 0.01322 0.00493 -0.0095 0.4819 0.0358
-3.500 -0.1512 0.01299 0.00468 -0.0092 0.4793 0.0366
-3.250 -0.1238 0.01282 0.00448 -0.0089 0.4768 0.0376
-3.000 -0.0961 0.01265 0.00431 -0.0086 0.4748 0.0389
-2.750 -0.0682 0.01248 0.00415 -0.0083 0.4728 0.0403
-2.500 -0.0404 0.01230 0.00399 -0.0081 0.4704 0.0422
-2.250 -0.0126 0.01215 0.00384 -0.0078 0.4678 0.0444
-2.000 0.0151 0.01200 0.00369 -0.0075 0.4651 0.0472
-1.750 0.0428 0.01187 0.00356 -0.0073 0.4626 0.0512
-1.500 0.0703 0.01175 0.00345 -0.0070 0.4604 0.0570
-1.250 0.0977 0.01164 0.00336 -0.0067 0.4581 0.0658
-1.000 0.1254 0.01151 0.00332 -0.0065 0.4560 0.0784
-0.750 0.1534 0.01143 0.00328 -0.0063 0.4535 0.0893
-0.500 0.1812 0.01134 0.00323 -0.0061 0.4509 0.0979
-0.250 0.2091 0.01128 0.00318 -0.0059 0.4484 0.1046
0.000 0.2368 0.01122 0.00314 -0.0057 0.4459 0.1118
0.250 0.2644 0.01116 0.00309 -0.0055 0.4432 0.1206
0.500 0.2916 0.01110 0.00306 -0.0052 0.4403 0.1354
0.750 0.3188 0.01098 0.00310 -0.0050 0.4372 0.1725
1.000 0.3464 0.01090 0.00312 -0.0048 0.4329 0.1978
1.250 0.3740 0.01086 0.00311 -0.0047 0.4283 0.2153
1.500 0.4016 0.01086 0.00310 -0.0045 0.4246 0.2268
1.750 0.4291 0.01086 0.00312 -0.0043 0.4220 0.2383
2.000 0.4568 0.01083 0.00314 -0.0041 0.4192 0.2497
2.500 0.5115 0.01077 0.00320 -0.0038 0.4124 0.2880
2.750 0.5362 0.01057 0.00323 -0.0032 0.4091 0.3689
3.250 0.5958 0.00932 0.00362 -0.0036 0.4031 0.9337
3.500 0.6331 0.00948 0.00377 -0.0053 0.3994 0.9430
3.750 0.6578 0.00961 0.00389 -0.0045 0.3959 0.9527
4.000 0.7025 0.00983 0.00405 -0.0079 0.3919 0.9573
4.250 0.7384 0.01001 0.00421 -0.0094 0.3883 0.9619
4.500 0.7630 0.01014 0.00434 -0.0087 0.3848 0.9671
4.750 0.8049 0.01031 0.00450 -0.0116 0.3800 0.9696
5.000 0.8429 0.01049 0.00463 -0.0137 0.3750 0.9720
5.250 0.8772 0.01065 0.00477 -0.0151 0.3700 0.9744
5.500 0.9081 0.01080 0.00492 -0.0158 0.3639 0.9770
5.750 0.9346 0.01098 0.00506 -0.0157 0.3583 0.9790
6.000 0.9636 0.01115 0.00523 -0.0160 0.3529 0.9812
6.250 0.9970 0.01131 0.00538 -0.0174 0.3467 0.9822
6.500 1.0277 0.01153 0.00556 -0.0183 0.3411 0.9832
6.750 1.0594 0.01169 0.00574 -0.0193 0.3355 0.9845
7.000 1.0918 0.01192 0.00595 -0.0205 0.3287 0.9863
7.250 1.1225 0.01217 0.00618 -0.0215 0.3219 0.9882
7.500 1.1514 0.01243 0.00644 -0.0221 0.3144 0.9899
7.750 1.1798 0.01274 0.00673 -0.0227 0.3080 0.9919
8.000 1.2098 0.01301 0.00700 -0.0235 0.3013 0.9933
8.250 1.2380 0.01337 0.00733 -0.0243 0.2943 0.9943
8.500 1.2653 0.01366 0.00763 -0.0247 0.2878 0.9953
8.750 1.2913 0.01407 0.00802 -0.0251 0.2804 0.9965
9.000 1.3176 0.01444 0.00840 -0.0255 0.2744 0.9976
9.250 1.3434 0.01487 0.00883 -0.0259 0.2677 0.9988
9.500 1.3685 0.01541 0.00935 -0.0264 0.2610 0.9999
9.750 1.3853 0.01584 0.00981 -0.0251 0.2559 1.0000
10.000 1.3963 0.01642 0.01039 -0.0229 0.2506 1.0000
10.250 1.4029 0.01710 0.01107 -0.0202 0.2462 1.0000
10.500 1.4092 0.01769 0.01170 -0.0174 0.2424 1.0000
10.750 1.3947 0.01869 0.01275 -0.0121 0.2394 1.0000
11.000 1.3894 0.01988 0.01397 -0.0087 0.2362 1.0000
11.250 1.3875 0.02124 0.01535 -0.0063 0.2328 1.0000
11.500 1.3894 0.02257 0.01670 -0.0044 0.2300 1.0000
11.750 1.3962 0.02369 0.01788 -0.0030 0.2275 1.0000
12.000 1.4016 0.02500 0.01923 -0.0017 0.2243 1.0000
12.250 1.4048 0.02654 0.02081 -0.0004 0.2209 1.0000
12.500 1.4064 0.02829 0.02257 0.0007 0.2176 1.0000
12.750 1.4081 0.03008 0.02438 0.0017 0.2150 1.0000
13.000 1.4159 0.03144 0.02581 0.0024 0.2125 1.0000
13.250 1.4218 0.03299 0.02742 0.0031 0.2096 1.0000
13.500 1.4248 0.03482 0.02930 0.0038 0.2062 1.0000
13.750 1.4247 0.03697 0.03147 0.0044 0.2025 1.0000
14.000 1.4257 0.03905 0.03357 0.0050 0.1994 1.0000
14.250 1.4321 0.04073 0.03532 0.0053 0.1964 1.0000
14.500 1.4364 0.04267 0.03731 0.0056 0.1924 1.0000
14.750 1.4331 0.04539 0.04004 0.0058 0.1869 1.0000
15.000 1.4349 0.04766 0.04236 0.0060 0.1820 1.0000
15.250 1.4342 0.05024 0.04495 0.0060 0.1752 1.0000
15.500 1.4310 0.05311 0.04784 0.0060 0.1693 1.0000
15.750 1.4266 0.05616 0.05090 0.0059 0.1610 1.0000
16.000 1.4222 0.05927 0.05402 0.0057 0.1538 1.0000
16.250 1.4126 0.06301 0.05774 0.0054 0.1456 1.0000
16.500 1.4052 0.06656 0.06130 0.0051 0.1380 1.0000
16.750 1.3977 0.07020 0.06494 0.0046 0.1326 1.0000
17.000 1.3865 0.07431 0.06905 0.0041 0.1252 1.0000
17.250 1.3819 0.07770 0.07246 0.0036 0.1212 1.0000
17.500 1.3764 0.08126 0.07605 0.0030 0.1163 1.0000
17.750 1.3714 0.08476 0.07958 0.0023 0.1127 1.0000
18.000 1.3667 0.08831 0.08316 0.0016 0.1090 1.0000
18.250 1.3640 0.09161 0.08651 0.0010 0.1049 1.0000
18.500 1.3565 0.09560 0.09053 0.0000 0.1009 1.0000
18.750 1.3546 0.09885 0.09383 -0.0007 0.0973 1.0000
19.000 1.3492 0.10264 0.09766 -0.0017 0.0918 1.0000
19.250 1.3436 0.10648 0.10153 -0.0028 0.0862 1.0000
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