GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 500,000 Max Cl/Cd: 94.46 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe701-il-500000-n5.txt Download as CSV file: xf-goe701-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9261 0.03156 0.02795 -0.1145 0.9832 0.0251
-13.750 -0.9158 0.02914 0.02536 -0.1149 0.9778 0.0260
-13.500 -0.8958 0.02733 0.02336 -0.1161 0.9747 0.0272
-13.250 -0.8722 0.02576 0.02161 -0.1174 0.9725 0.0283
-13.000 -0.8469 0.02462 0.02039 -0.1184 0.9704 0.0293
-12.750 -0.8273 0.02376 0.01944 -0.1178 0.9655 0.0304
-12.500 -0.8018 0.02283 0.01838 -0.1184 0.9627 0.0315
-12.250 -0.7734 0.02192 0.01729 -0.1195 0.9605 0.0325
-12.000 -0.7438 0.02107 0.01636 -0.1207 0.9587 0.0335
-11.750 -0.7196 0.02050 0.01574 -0.1206 0.9546 0.0344
-11.500 -0.6951 0.01995 0.01511 -0.1204 0.9499 0.0354
-11.250 -0.6666 0.01936 0.01441 -0.1210 0.9465 0.0365
-11.000 -0.6359 0.01876 0.01367 -0.1220 0.9439 0.0375
-10.750 -0.6134 0.01821 0.01301 -0.1213 0.9380 0.0383
-10.500 -0.5888 0.01763 0.01239 -0.1210 0.9324 0.0392
-10.250 -0.5591 0.01714 0.01184 -0.1217 0.9284 0.0401
-10.000 -0.5347 0.01679 0.01142 -0.1211 0.9219 0.0412
-9.750 -0.5082 0.01638 0.01093 -0.1210 0.9155 0.0422
-9.500 -0.4792 0.01600 0.01043 -0.1213 0.9103 0.0434
-9.250 -0.4548 0.01567 0.00998 -0.1207 0.9021 0.0442
-9.000 -0.4284 0.01504 0.00928 -0.1206 0.8954 0.0452
-8.750 -0.4045 0.01461 0.00879 -0.1199 0.8865 0.0460
-8.500 -0.3773 0.01421 0.00831 -0.1199 0.8790 0.0468
-8.250 -0.3521 0.01389 0.00791 -0.1193 0.8700 0.0478
-8.000 -0.3255 0.01356 0.00748 -0.1191 0.8619 0.0488
-7.750 -0.2999 0.01325 0.00708 -0.1185 0.8528 0.0497
-7.500 -0.2739 0.01296 0.00667 -0.1181 0.8446 0.0504
-7.250 -0.2482 0.01270 0.00631 -0.1176 0.8359 0.0511
-7.000 -0.2230 0.01237 0.00591 -0.1170 0.8280 0.0521
-6.750 -0.1981 0.01206 0.00554 -0.1164 0.8197 0.0533
-6.500 -0.1724 0.01182 0.00524 -0.1159 0.8124 0.0546
-6.250 -0.1468 0.01161 0.00497 -0.1153 0.8047 0.0560
-6.000 -0.1208 0.01142 0.00470 -0.1148 0.7979 0.0573
-5.750 -0.0951 0.01123 0.00445 -0.1142 0.7906 0.0586
-5.500 -0.0691 0.01107 0.00421 -0.1137 0.7839 0.0596
-5.250 -0.0435 0.01085 0.00397 -0.1132 0.7774 0.0617
-5.000 -0.0177 0.01068 0.00378 -0.1126 0.7706 0.0640
-4.750 0.0085 0.01054 0.00359 -0.1121 0.7645 0.0666
-4.500 0.0345 0.01040 0.00343 -0.1116 0.7579 0.0693
-4.250 0.0605 0.01027 0.00330 -0.1111 0.7515 0.0733
-4.000 0.0868 0.01018 0.00317 -0.1107 0.7455 0.0776
-3.750 0.1130 0.01007 0.00308 -0.1102 0.7389 0.0824
-3.500 0.1393 0.01002 0.00299 -0.1097 0.7329 0.0877
-3.250 0.1657 0.00994 0.00290 -0.1093 0.7269 0.0922
-3.000 0.1919 0.00988 0.00283 -0.1088 0.7203 0.0970
-2.750 0.2183 0.00985 0.00275 -0.1083 0.7142 0.1009
-2.500 0.2447 0.00981 0.00268 -0.1078 0.7077 0.1033
-2.250 0.2704 0.00972 0.00259 -0.1073 0.7011 0.1073
-2.000 0.2965 0.00967 0.00253 -0.1068 0.6949 0.1111
-1.750 0.3223 0.00963 0.00247 -0.1062 0.6870 0.1146
-1.500 0.3480 0.00962 0.00241 -0.1056 0.6791 0.1173
-1.250 0.3732 0.00958 0.00235 -0.1049 0.6693 0.1200
-1.000 0.3984 0.00954 0.00230 -0.1042 0.6607 0.1240
-0.750 0.4232 0.00952 0.00226 -0.1034 0.6505 0.1285
-0.500 0.4480 0.00952 0.00223 -0.1027 0.6391 0.1332
-0.250 0.4722 0.00952 0.00221 -0.1018 0.6273 0.1388
0.000 0.4960 0.00953 0.00220 -0.1008 0.6146 0.1453
0.250 0.5202 0.00955 0.00220 -0.0999 0.6021 0.1530
0.500 0.5446 0.00956 0.00222 -0.0991 0.5913 0.1627
0.750 0.5685 0.00959 0.00224 -0.0982 0.5805 0.1740
1.000 0.5924 0.00963 0.00227 -0.0973 0.5689 0.1849
1.250 0.6164 0.00967 0.00231 -0.0964 0.5579 0.1962
1.500 0.6398 0.00971 0.00236 -0.0954 0.5475 0.2075
1.750 0.6633 0.00977 0.00241 -0.0944 0.5363 0.2192
2.250 0.7090 0.00988 0.00254 -0.0923 0.5133 0.2517
2.500 0.7303 0.00993 0.00264 -0.0909 0.5002 0.2834
2.750 0.7509 0.00992 0.00275 -0.0895 0.4860 0.3482
3.000 0.7704 0.00985 0.00287 -0.0878 0.4725 0.4379
3.500 0.8944 0.00949 0.00363 -0.1031 0.4303 0.9958
3.750 0.9257 0.00980 0.00382 -0.1041 0.4083 1.0000
4.000 0.9413 0.01007 0.00399 -0.1016 0.3895 1.0000
4.250 0.9566 0.01035 0.00417 -0.0990 0.3712 1.0000
4.500 0.9718 0.01063 0.00436 -0.0965 0.3536 1.0000
4.750 0.9866 0.01092 0.00456 -0.0939 0.3359 1.0000
5.000 1.0001 0.01123 0.00478 -0.0910 0.3182 1.0000
5.250 1.0117 0.01155 0.00501 -0.0878 0.3011 1.0000
5.500 1.0238 0.01187 0.00524 -0.0847 0.2856 1.0000
5.750 1.0368 0.01220 0.00550 -0.0818 0.2722 1.0000
6.000 1.0510 0.01252 0.00576 -0.0793 0.2603 1.0000
6.250 1.0665 0.01282 0.00603 -0.0770 0.2510 1.0000
6.500 1.0812 0.01319 0.00634 -0.0746 0.2415 1.0000
6.750 1.0977 0.01350 0.00662 -0.0725 0.2330 1.0000
7.000 1.1133 0.01387 0.00696 -0.0704 0.2262 1.0000
7.250 1.1309 0.01417 0.00726 -0.0687 0.2206 1.0000
7.500 1.1477 0.01452 0.00760 -0.0668 0.2147 1.0000
7.750 1.1635 0.01493 0.00798 -0.0649 0.2089 1.0000
8.000 1.1814 0.01526 0.00833 -0.0633 0.2036 1.0000
8.250 1.1981 0.01565 0.00871 -0.0616 0.1985 1.0000
8.500 1.2137 0.01610 0.00916 -0.0597 0.1939 1.0000
8.750 1.2319 0.01645 0.00954 -0.0583 0.1898 1.0000
9.000 1.2487 0.01688 0.00998 -0.0567 0.1845 1.0000
9.250 1.2636 0.01741 0.01050 -0.0549 0.1790 1.0000
9.500 1.2809 0.01784 0.01096 -0.0535 0.1736 1.0000
9.750 1.2963 0.01838 0.01149 -0.0519 0.1672 1.0000
10.000 1.3115 0.01895 0.01207 -0.0503 0.1613 1.0000
10.250 1.3253 0.01961 0.01270 -0.0486 0.1520 1.0000
10.500 1.3392 0.02029 0.01338 -0.0470 0.1434 1.0000
10.750 1.3512 0.02110 0.01415 -0.0452 0.1335 1.0000
11.000 1.3619 0.02202 0.01503 -0.0434 0.1230 1.0000
11.250 1.3717 0.02303 0.01600 -0.0416 0.1120 1.0000
11.500 1.3803 0.02415 0.01707 -0.0397 0.1008 1.0000
11.750 1.3898 0.02524 0.01815 -0.0381 0.0925 1.0000
12.000 1.3966 0.02656 0.01944 -0.0363 0.0822 1.0000
12.250 1.4025 0.02798 0.02083 -0.0345 0.0712 1.0000
12.500 1.3925 0.03067 0.02329 -0.0316 0.0393 1.0000
12.750 1.3941 0.03257 0.02520 -0.0299 0.0327 1.0000
13.000 1.4001 0.03417 0.02684 -0.0285 0.0299 1.0000
13.250 1.4062 0.03581 0.02853 -0.0273 0.0281 1.0000
13.500 1.4107 0.03764 0.03042 -0.0261 0.0263 1.0000
13.750 1.4185 0.03921 0.03207 -0.0252 0.0253 1.0000
14.000 1.4242 0.04100 0.03394 -0.0242 0.0240 1.0000
14.250 1.4286 0.04297 0.03598 -0.0233 0.0230 1.0000
14.500 1.4314 0.04515 0.03823 -0.0225 0.0221 1.0000
14.750 1.4356 0.04725 0.04040 -0.0219 0.0212 1.0000
15.000 1.4400 0.04936 0.04260 -0.0213 0.0203 1.0000
15.250 1.4426 0.05172 0.04505 -0.0208 0.0198 1.0000
15.500 1.4439 0.05428 0.04769 -0.0204 0.0190 1.0000
15.750 1.4438 0.05707 0.05055 -0.0202 0.0184 1.0000
16.000 1.4410 0.06024 0.05380 -0.0200 0.0178 1.0000
16.250 1.4415 0.06308 0.05674 -0.0200 0.0174 1.0000
16.500 1.4400 0.06623 0.05999 -0.0201 0.0169 1.0000
16.750 1.4380 0.06952 0.06337 -0.0203 0.0164 1.0000
17.000 1.4341 0.07310 0.06705 -0.0207 0.0159 1.0000
17.250 1.4292 0.07687 0.07091 -0.0212 0.0155 1.0000
17.500 1.4220 0.08104 0.07518 -0.0219 0.0152 1.0000
17.750 1.4136 0.08547 0.07972 -0.0228 0.0149 1.0000
18.000 1.4032 0.09028 0.08463 -0.0239 0.0147 1.0000
18.250 1.3935 0.09504 0.08951 -0.0251 0.0143 1.0000
18.500 1.3846 0.09977 0.09435 -0.0265 0.0141 1.0000
18.750 1.3732 0.10499 0.09968 -0.0281 0.0139 1.0000
19.000 1.3618 0.11027 0.10509 -0.0298 0.0137 1.0000
19.250 1.3511 0.11548 0.11041 -0.0316 0.0133 1.0000
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Polar data table (+)
Polar graphs
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