GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.59 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe723-il-1000000.txt Download as CSV file: xf-goe723-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3176 0.08600 0.08430 -0.0490 0.9975 0.0254
-9.000 -0.3033 0.08139 0.07969 -0.0543 0.9936 0.0260
-8.750 -0.3840 0.03703 0.03461 -0.1104 0.9487 0.0285
-8.500 -0.3425 0.03438 0.03192 -0.1165 0.9400 0.0288
-8.250 -0.3007 0.03185 0.02924 -0.1230 0.9237 0.0292
-8.000 -0.2726 0.02964 0.02678 -0.1262 0.8979 0.0296
-7.750 -0.2553 0.02809 0.02500 -0.1261 0.8745 0.0302
-7.500 -0.2396 0.02666 0.02333 -0.1253 0.8538 0.0311
-7.250 -0.2178 0.02759 0.02384 -0.1239 0.8352 0.0330
-7.000 -0.2016 0.02629 0.02225 -0.1227 0.8192 0.0331
-6.750 -0.1971 0.02095 0.01651 -0.1213 0.8044 0.0341
-6.500 -0.1756 0.01988 0.01535 -0.1205 0.7913 0.0344
-6.000 -0.1389 0.01496 0.00955 -0.1171 0.7679 0.0286
-5.750 -0.1155 0.01411 0.00858 -0.1163 0.7580 0.0287
-5.500 -0.0915 0.01342 0.00778 -0.1155 0.7485 0.0289
-5.250 -0.0670 0.01280 0.00709 -0.1149 0.7399 0.0290
-5.000 -0.0423 0.01230 0.00651 -0.1142 0.7311 0.0292
-4.750 -0.0172 0.01183 0.00599 -0.1136 0.7232 0.0294
-4.500 0.0079 0.01141 0.00550 -0.1129 0.7155 0.0296
-4.250 0.0332 0.01101 0.00506 -0.1123 0.7086 0.0298
-4.000 0.0587 0.01065 0.00465 -0.1117 0.7013 0.0300
-3.750 0.0838 0.01034 0.00428 -0.1111 0.6944 0.0302
-3.500 0.1097 0.01002 0.00395 -0.1105 0.6877 0.0306
-3.250 0.1354 0.00978 0.00366 -0.1100 0.6811 0.0311
-3.000 0.1615 0.00957 0.00342 -0.1095 0.6750 0.0317
-2.750 0.1876 0.00935 0.00316 -0.1090 0.6684 0.0321
-2.500 0.2134 0.00918 0.00293 -0.1084 0.6618 0.0325
-2.250 0.2401 0.00901 0.00275 -0.1080 0.6554 0.0329
-2.000 0.2662 0.00889 0.00257 -0.1074 0.6475 0.0331
-1.750 0.2917 0.00860 0.00224 -0.1068 0.6399 0.0338
-1.500 0.3177 0.00843 0.00201 -0.1063 0.6320 0.0346
-1.250 0.3442 0.00831 0.00187 -0.1058 0.6259 0.0356
-1.000 0.3711 0.00821 0.00176 -0.1055 0.6197 0.0365
-0.750 0.3976 0.00815 0.00166 -0.1050 0.6134 0.0378
-0.500 0.4247 0.00809 0.00159 -0.1047 0.6076 0.0392
-0.250 0.4515 0.00800 0.00149 -0.1043 0.6016 0.0428
0.000 0.4778 0.00796 0.00143 -0.1038 0.5955 0.0492
0.250 0.5009 0.00728 0.00136 -0.1030 0.5900 0.2517
0.500 0.5264 0.00710 0.00140 -0.1025 0.5839 0.3353
0.750 0.5525 0.00708 0.00144 -0.1020 0.5782 0.3715
1.000 0.5795 0.00703 0.00148 -0.1017 0.5727 0.4012
1.250 0.6057 0.00701 0.00152 -0.1012 0.5664 0.4336
1.500 0.6319 0.00701 0.00156 -0.1008 0.5589 0.4617
1.750 0.6576 0.00701 0.00161 -0.1002 0.5488 0.4904
2.000 0.6834 0.00699 0.00167 -0.0997 0.5397 0.5302
2.250 0.7085 0.00697 0.00174 -0.0990 0.5320 0.5751
2.500 0.7331 0.00687 0.00181 -0.0982 0.5245 0.6419
2.750 0.8355 0.00636 0.00201 -0.1151 0.5094 1.0000
3.000 0.8612 0.00647 0.00208 -0.1146 0.5004 1.0000
3.250 0.8870 0.00658 0.00215 -0.1140 0.4901 1.0000
3.500 0.9121 0.00672 0.00224 -0.1134 0.4793 1.0000
3.750 0.9370 0.00686 0.00233 -0.1127 0.4664 1.0000
4.000 0.9614 0.00704 0.00243 -0.1119 0.4497 1.0000
4.250 0.9857 0.00723 0.00255 -0.1111 0.4320 1.0000
4.500 1.0095 0.00744 0.00269 -0.1102 0.4126 1.0000
4.750 1.0324 0.00770 0.00285 -0.1092 0.3906 1.0000
5.000 1.0546 0.00801 0.00305 -0.1080 0.3672 1.0000
5.250 1.0754 0.00840 0.00329 -0.1067 0.3392 1.0000
5.500 1.0960 0.00879 0.00354 -0.1053 0.3110 1.0000
5.750 1.1165 0.00920 0.00382 -0.1038 0.2837 1.0000
6.000 1.1339 0.00977 0.00417 -0.1019 0.2436 1.0000
6.250 1.1340 0.01137 0.00511 -0.0971 0.1272 1.0000
6.500 1.1488 0.01207 0.00564 -0.0947 0.0937 1.0000
6.750 1.1652 0.01266 0.00608 -0.0927 0.0697 1.0000
7.000 1.1848 0.01305 0.00642 -0.0912 0.0631 1.0000
7.250 1.2036 0.01347 0.00681 -0.0895 0.0587 1.0000
7.500 1.2232 0.01383 0.00718 -0.0880 0.0563 1.0000
7.750 1.2433 0.01414 0.00751 -0.0866 0.0550 1.0000
8.000 1.2625 0.01449 0.00789 -0.0851 0.0534 1.0000
8.250 1.2791 0.01489 0.00830 -0.0830 0.0515 1.0000
8.500 1.2924 0.01536 0.00878 -0.0804 0.0494 1.0000
8.750 1.3050 0.01587 0.00933 -0.0777 0.0477 1.0000
9.000 1.3224 0.01620 0.00968 -0.0760 0.0471 1.0000
9.250 1.3391 0.01657 0.01009 -0.0741 0.0461 1.0000
9.500 1.3549 0.01701 0.01056 -0.0722 0.0451 1.0000
9.750 1.3705 0.01747 0.01105 -0.0704 0.0438 1.0000
10.000 1.3844 0.01804 0.01163 -0.0683 0.0427 1.0000
10.250 1.3954 0.01879 0.01240 -0.0660 0.0413 1.0000
10.500 1.4050 0.01965 0.01332 -0.0636 0.0401 1.0000
10.750 1.4231 0.02006 0.01377 -0.0625 0.0394 1.0000
11.000 1.4385 0.02065 0.01439 -0.0610 0.0384 1.0000
11.250 1.4531 0.02130 0.01508 -0.0596 0.0373 1.0000
11.500 1.4667 0.02206 0.01585 -0.0581 0.0362 1.0000
11.750 1.4776 0.02302 0.01683 -0.0565 0.0350 1.0000
12.000 1.4851 0.02428 0.01814 -0.0546 0.0338 1.0000
12.250 1.5012 0.02495 0.01886 -0.0537 0.0329 1.0000
12.500 1.5155 0.02578 0.01973 -0.0526 0.0317 1.0000
12.750 1.5279 0.02679 0.02075 -0.0515 0.0304 1.0000
13.000 1.5358 0.02819 0.02216 -0.0502 0.0290 1.0000
13.250 1.5458 0.02946 0.02349 -0.0491 0.0279 1.0000
13.500 1.5570 0.03066 0.02474 -0.0481 0.0268 1.0000
13.750 1.5662 0.03206 0.02616 -0.0472 0.0255 1.0000
14.000 1.5710 0.03389 0.02802 -0.0461 0.0243 1.0000
14.250 1.5773 0.03563 0.02983 -0.0451 0.0234 1.0000
14.500 1.5848 0.03727 0.03153 -0.0443 0.0224 1.0000
14.750 1.5903 0.03913 0.03342 -0.0435 0.0214 1.0000
15.000 1.5922 0.04141 0.03573 -0.0427 0.0203 1.0000
15.250 1.5927 0.04388 0.03827 -0.0419 0.0197 1.0000
15.500 1.5966 0.04603 0.04051 -0.0413 0.0192 1.0000
15.750 1.5990 0.04840 0.04295 -0.0408 0.0186 1.0000
16.000 1.6006 0.05091 0.04552 -0.0404 0.0181 1.0000
16.250 1.6001 0.05370 0.04836 -0.0400 0.0175 1.0000
16.500 1.5966 0.05691 0.05163 -0.0398 0.0170 1.0000
16.750 1.5904 0.06053 0.05533 -0.0397 0.0165 1.0000
17.000 1.5913 0.06335 0.05824 -0.0396 0.0163 1.0000
17.250 1.5910 0.06633 0.06130 -0.0397 0.0159 1.0000
17.500 1.5897 0.06948 0.06454 -0.0398 0.0155 1.0000
17.750 1.5876 0.07280 0.06794 -0.0400 0.0152 1.0000
18.000 1.5845 0.07630 0.07153 -0.0404 0.0150 1.0000
18.250 1.5809 0.07989 0.07517 -0.0408 0.0146 1.0000
18.500 1.5759 0.08371 0.07907 -0.0414 0.0144 1.0000
18.750 1.5671 0.08814 0.08358 -0.0422 0.0140 1.0000
19.000 1.5564 0.09293 0.08846 -0.0432 0.0137 1.0000
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