GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.97 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe704-il-1000000-n5.txt Download as CSV file: xf-goe704-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0266 0.10110 0.09840 -0.0084 1.0000 0.0064
-16.500 -1.2800 0.04926 0.04577 -0.0433 1.0000 0.0055
-16.250 -1.3124 0.04126 0.03750 -0.0480 1.0000 0.0054
-16.000 -1.3242 0.03774 0.03383 -0.0476 1.0000 0.0055
-15.750 -1.3298 0.03523 0.03118 -0.0462 1.0000 0.0055
-15.500 -1.3312 0.03326 0.02909 -0.0443 1.0000 0.0055
-15.250 -1.3348 0.03125 0.02695 -0.0417 1.0000 0.0057
-15.000 -1.3344 0.02962 0.02521 -0.0390 1.0000 0.0058
-14.750 -1.3308 0.02828 0.02377 -0.0363 1.0000 0.0059
-14.500 -1.3249 0.02714 0.02254 -0.0336 1.0000 0.0060
-14.250 -1.3155 0.02613 0.02144 -0.0312 1.0000 0.0062
-14.000 -1.3024 0.02517 0.02041 -0.0294 1.0000 0.0064
-13.750 -1.2875 0.02427 0.01943 -0.0279 1.0000 0.0065
-13.500 -1.2711 0.02344 0.01852 -0.0264 1.0000 0.0067
-13.250 -1.2537 0.02264 0.01765 -0.0251 1.0000 0.0068
-13.000 -1.2352 0.02189 0.01681 -0.0239 1.0000 0.0070
-12.750 -1.2158 0.02119 0.01604 -0.0228 1.0000 0.0072
-12.500 -1.1957 0.02052 0.01530 -0.0218 1.0000 0.0074
-12.250 -1.1747 0.01990 0.01462 -0.0209 1.0000 0.0075
-12.000 -1.1544 0.01918 0.01382 -0.0199 1.0000 0.0078
-11.750 -1.1324 0.01849 0.01308 -0.0192 0.9948 0.0081
-11.500 -1.1052 0.01786 0.01238 -0.0195 0.9733 0.0085
-11.250 -1.0814 0.01733 0.01178 -0.0189 0.9505 0.0089
-11.000 -1.0607 0.01690 0.01125 -0.0176 0.9272 0.0092
-10.750 -1.0392 0.01650 0.01074 -0.0164 0.9052 0.0096
-10.500 -1.0165 0.01613 0.01026 -0.0155 0.8856 0.0099
-10.250 -0.9937 0.01567 0.00970 -0.0146 0.8681 0.0106
-10.000 -0.9702 0.01524 0.00917 -0.0138 0.8517 0.0113
-9.750 -0.9459 0.01486 0.00870 -0.0132 0.8365 0.0120
-9.500 -0.9210 0.01451 0.00826 -0.0127 0.8231 0.0127
-9.250 -0.8958 0.01415 0.00783 -0.0123 0.8118 0.0137
-9.000 -0.8706 0.01377 0.00739 -0.0118 0.8013 0.0151
-8.750 -0.8449 0.01343 0.00699 -0.0114 0.7913 0.0168
-8.500 -0.8194 0.01305 0.00658 -0.0111 0.7826 0.0199
-8.250 -0.7937 0.01267 0.00619 -0.0107 0.7745 0.0243
-8.000 -0.7675 0.01235 0.00585 -0.0104 0.7677 0.0285
-7.750 -0.7410 0.01206 0.00554 -0.0102 0.7607 0.0323
-7.250 -0.6876 0.01151 0.00495 -0.0098 0.7488 0.0404
-7.000 -0.6609 0.01123 0.00467 -0.0096 0.7434 0.0457
-6.500 -0.6067 0.01075 0.00417 -0.0093 0.7335 0.0556
-6.250 -0.5795 0.01050 0.00394 -0.0092 0.7287 0.0627
-6.000 -0.5523 0.01028 0.00374 -0.0091 0.7242 0.0715
-5.750 -0.5248 0.01008 0.00356 -0.0090 0.7201 0.0806
-5.500 -0.4972 0.00989 0.00341 -0.0090 0.7159 0.0905
-5.250 -0.4692 0.00976 0.00327 -0.0090 0.7117 0.0958
-5.000 -0.4412 0.00963 0.00313 -0.0090 0.7076 0.1003
-4.750 -0.4130 0.00951 0.00300 -0.0090 0.7038 0.1037
-4.500 -0.3846 0.00942 0.00288 -0.0090 0.6999 0.1061
-4.250 -0.3564 0.00930 0.00276 -0.0091 0.6956 0.1100
-4.000 -0.3282 0.00919 0.00264 -0.0091 0.6915 0.1139
-3.750 -0.2998 0.00909 0.00254 -0.0092 0.6872 0.1175
-3.500 -0.2713 0.00901 0.00243 -0.0092 0.6803 0.1200
-3.250 -0.2431 0.00894 0.00232 -0.0093 0.6717 0.1233
-3.000 -0.2148 0.00884 0.00222 -0.0093 0.6628 0.1280
-2.750 -0.1864 0.00876 0.00214 -0.0094 0.6572 0.1327
-2.500 -0.1577 0.00869 0.00206 -0.0095 0.6518 0.1358
-2.250 -0.1293 0.00861 0.00197 -0.0095 0.6461 0.1402
-2.000 -0.1009 0.00853 0.00190 -0.0096 0.6406 0.1447
-1.750 -0.0722 0.00846 0.00183 -0.0097 0.6343 0.1489
-1.500 -0.0437 0.00842 0.00176 -0.0099 0.6275 0.1527
-1.250 -0.0152 0.00833 0.00170 -0.0100 0.6205 0.1594
-1.000 0.0132 0.00829 0.00165 -0.0100 0.6108 0.1662
-0.750 0.0414 0.00822 0.00159 -0.0101 0.5978 0.1774
-0.500 0.0694 0.00818 0.00154 -0.0101 0.5808 0.1914
-0.250 0.0972 0.00813 0.00151 -0.0102 0.5627 0.2120
0.000 0.1248 0.00807 0.00149 -0.0102 0.5455 0.2380
0.250 0.1525 0.00805 0.00148 -0.0102 0.5256 0.2632
0.500 0.1799 0.00807 0.00149 -0.0102 0.5018 0.2872
0.750 0.2074 0.00811 0.00151 -0.0102 0.4768 0.3102
1.000 0.2346 0.00814 0.00154 -0.0101 0.4529 0.3364
1.250 0.2614 0.00818 0.00159 -0.0101 0.4271 0.3712
1.500 0.2871 0.00818 0.00165 -0.0098 0.3957 0.4307
1.750 0.3117 0.00806 0.00170 -0.0094 0.3681 0.5218
2.000 0.3234 0.00700 0.00173 -0.0061 0.3524 0.8583
2.250 0.3498 0.00714 0.00186 -0.0057 0.3341 0.8858
2.750 0.4033 0.00748 0.00211 -0.0052 0.3012 0.9154
3.000 0.4300 0.00763 0.00224 -0.0049 0.2884 0.9258
3.250 0.4571 0.00779 0.00236 -0.0047 0.2765 0.9325
3.500 0.4834 0.00796 0.00249 -0.0044 0.2647 0.9400
3.750 0.5100 0.00813 0.00260 -0.0042 0.2538 0.9451
4.000 0.5369 0.00829 0.00274 -0.0039 0.2435 0.9500
4.250 0.5629 0.00847 0.00288 -0.0035 0.2341 0.9556
4.500 0.5888 0.00865 0.00302 -0.0032 0.2243 0.9596
4.750 0.6167 0.00881 0.00315 -0.0033 0.2156 0.9620
5.000 0.6440 0.00899 0.00330 -0.0032 0.2075 0.9650
5.250 0.6711 0.00917 0.00346 -0.0031 0.2000 0.9683
5.500 0.6973 0.00934 0.00360 -0.0029 0.1935 0.9710
5.750 0.7245 0.00949 0.00374 -0.0030 0.1878 0.9726
6.250 0.7813 0.00985 0.00407 -0.0036 0.1754 0.9746
6.500 0.8093 0.01006 0.00425 -0.0039 0.1687 0.9757
6.750 0.8372 0.01027 0.00445 -0.0041 0.1608 0.9769
7.000 0.8645 0.01053 0.00466 -0.0043 0.1522 0.9782
7.250 0.8919 0.01075 0.00487 -0.0045 0.1440 0.9797
7.500 0.9175 0.01109 0.00513 -0.0044 0.1286 0.9814
7.750 0.9380 0.01178 0.00559 -0.0036 0.0924 0.9839
8.000 0.9656 0.01217 0.00594 -0.0040 0.0838 0.9848
8.250 0.9934 0.01250 0.00626 -0.0045 0.0797 0.9858
8.500 1.0211 0.01284 0.00660 -0.0049 0.0748 0.9868
8.750 1.0491 0.01311 0.00689 -0.0053 0.0718 0.9878
9.000 1.0759 0.01348 0.00726 -0.0056 0.0663 0.9889
9.250 1.1022 0.01388 0.00764 -0.0058 0.0594 0.9901
9.500 1.1179 0.01518 0.00865 -0.0048 0.0216 0.9925
9.750 1.1405 0.01579 0.00924 -0.0044 0.0160 0.9941
10.000 1.1660 0.01630 0.00977 -0.0047 0.0138 0.9949
10.250 1.1909 0.01683 0.01031 -0.0049 0.0124 0.9960
10.500 1.2147 0.01740 0.01091 -0.0049 0.0113 0.9973
10.750 1.2391 0.01791 0.01146 -0.0051 0.0107 0.9988
11.000 1.2578 0.01844 0.01203 -0.0041 0.0101 1.0000
11.250 1.2547 0.01882 0.01244 0.0013 0.0098 1.0000
11.500 1.2606 0.01938 0.01303 0.0046 0.0093 1.0000
11.750 1.2704 0.02009 0.01377 0.0069 0.0088 1.0000
12.000 1.2820 0.02086 0.01459 0.0086 0.0084 1.0000
12.250 1.2952 0.02163 0.01540 0.0100 0.0081 1.0000
12.500 1.3080 0.02248 0.01631 0.0112 0.0079 1.0000
12.750 1.3204 0.02342 0.01731 0.0124 0.0076 1.0000
13.000 1.3323 0.02446 0.01840 0.0134 0.0073 1.0000
13.250 1.3433 0.02562 0.01960 0.0143 0.0071 1.0000
13.500 1.3534 0.02689 0.02092 0.0152 0.0068 1.0000
13.750 1.3621 0.02834 0.02243 0.0160 0.0066 1.0000
14.000 1.3687 0.03001 0.02416 0.0168 0.0063 1.0000
14.250 1.3767 0.03160 0.02583 0.0174 0.0062 1.0000
14.500 1.3844 0.03327 0.02757 0.0179 0.0061 1.0000
14.750 1.3908 0.03508 0.02946 0.0184 0.0060 1.0000
15.000 1.3961 0.03704 0.03149 0.0187 0.0058 1.0000
15.250 1.4004 0.03915 0.03368 0.0190 0.0057 1.0000
15.500 1.4032 0.04145 0.03606 0.0192 0.0056 1.0000
15.750 1.4048 0.04392 0.03861 0.0193 0.0055 1.0000
16.000 1.4051 0.04663 0.04139 0.0192 0.0053 1.0000
16.250 1.4042 0.04959 0.04444 0.0189 0.0052 1.0000
16.500 1.4017 0.05284 0.04778 0.0184 0.0051 1.0000
16.750 1.3975 0.05645 0.05148 0.0177 0.0051 1.0000
17.000 1.3917 0.06042 0.05555 0.0167 0.0050 1.0000
17.250 1.3838 0.06478 0.06001 0.0155 0.0049 1.0000
17.500 1.3734 0.06964 0.06499 0.0139 0.0048 1.0000
17.750 1.3610 0.07496 0.07043 0.0121 0.0048 1.0000
18.000 1.3461 0.08075 0.07634 0.0100 0.0048 1.0000
18.250 1.3293 0.08693 0.08264 0.0076 0.0047 1.0000
18.500 1.3111 0.09348 0.08931 0.0051 0.0047 1.0000
18.750 1.2921 0.10018 0.09613 0.0024 0.0047 1.0000
19.000 1.2723 0.10713 0.10320 -0.0005 0.0047 1.0000
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