FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 500,000 Max Cl/Cd: 110.08 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66196v-il-500000.txt Download as CSV file: xf-fx66196v-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 V1 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4647 0.08409 0.08159 -0.0858 0.9469 0.0153
-14.500 -0.3926 0.08427 0.08178 -0.0953 0.9217 0.0159
-14.250 -0.4857 0.06180 0.05859 -0.1126 0.9137 0.0145
-14.000 -0.4939 0.05453 0.05089 -0.1218 0.8837 0.0146
-13.750 -0.5036 0.05027 0.04629 -0.1248 0.8560 0.0146
-13.500 -0.5192 0.04636 0.04206 -0.1260 0.8340 0.0147
-13.250 -0.5245 0.04418 0.03965 -0.1264 0.8155 0.0148
-13.000 -0.5334 0.04109 0.03632 -0.1262 0.8001 0.0147
-12.750 -0.5478 0.03751 0.03244 -0.1257 0.7860 0.0150
-12.500 -0.5481 0.03521 0.02995 -0.1249 0.7726 0.0152
-12.250 -0.5437 0.03348 0.02808 -0.1241 0.7605 0.0154
-12.000 -0.5378 0.03211 0.02659 -0.1234 0.7485 0.0157
-11.500 -0.5236 0.02947 0.02367 -0.1216 0.7272 0.0162
-11.250 -0.5142 0.02833 0.02239 -0.1206 0.7178 0.0166
-11.000 -0.5033 0.02708 0.02099 -0.1194 0.7085 0.0168
-10.750 -0.4919 0.02602 0.01980 -0.1184 0.7003 0.0173
-10.500 -0.4787 0.02496 0.01859 -0.1172 0.6923 0.0175
-10.250 -0.4658 0.02403 0.01753 -0.1160 0.6849 0.0180
-10.000 -0.4526 0.02317 0.01654 -0.1148 0.6775 0.0183
-9.750 -0.4405 0.02248 0.01572 -0.1134 0.6709 0.0187
-9.500 -0.4279 0.02110 0.01428 -0.1117 0.6645 0.0193
-9.250 -0.4205 0.02031 0.01343 -0.1095 0.6587 0.0198
-9.000 -0.4084 0.01973 0.01283 -0.1079 0.6527 0.0205
-8.750 -0.3927 0.01921 0.01224 -0.1068 0.6472 0.0214
-8.500 -0.3755 0.01872 0.01165 -0.1057 0.6421 0.0225
-8.250 -0.3568 0.01821 0.01108 -0.1048 0.6369 0.0232
-8.000 -0.3446 0.01725 0.01004 -0.1032 0.6322 0.0243
-7.750 -0.3270 0.01666 0.00939 -0.1023 0.6278 0.0255
-7.500 -0.3061 0.01618 0.00889 -0.1017 0.6234 0.0271
-7.250 -0.2842 0.01575 0.00839 -0.1012 0.6190 0.0287
-7.000 -0.2650 0.01508 0.00766 -0.1005 0.6151 0.0312
-6.750 -0.2417 0.01473 0.00724 -0.1002 0.6114 0.0343
-6.500 -0.2188 0.01421 0.00670 -0.0999 0.6078 0.0383
-6.250 -0.1945 0.01382 0.00628 -0.0997 0.6042 0.0438
-6.000 -0.1705 0.01337 0.00583 -0.0996 0.6009 0.0538
-5.750 -0.1469 0.01286 0.00537 -0.0995 0.5978 0.0766
-5.500 -0.1238 0.01217 0.00493 -0.0995 0.5950 0.1304
-5.250 -0.1017 0.01125 0.00441 -0.0995 0.5921 0.2282
-4.750 -0.0539 0.01000 0.00393 -0.0996 0.5866 0.4532
-4.500 -0.0252 0.01012 0.00395 -0.0999 0.5840 0.4757
-4.250 0.0037 0.01029 0.00400 -0.1002 0.5813 0.4905
-4.000 0.0322 0.01034 0.00406 -0.1004 0.5790 0.5008
-3.750 0.0608 0.01041 0.00408 -0.1006 0.5766 0.5100
-3.500 0.0895 0.01053 0.00416 -0.1009 0.5742 0.5190
-3.250 0.1181 0.01064 0.00422 -0.1011 0.5721 0.5273
-3.000 0.1468 0.01083 0.00435 -0.1013 0.5700 0.5366
-2.750 0.1753 0.01095 0.00444 -0.1015 0.5680 0.5436
-2.500 0.2044 0.01114 0.00455 -0.1018 0.5659 0.5494
-2.250 0.2331 0.01121 0.00456 -0.1022 0.5644 0.5536
-2.000 0.2616 0.01115 0.00451 -0.1025 0.5627 0.5564
-1.750 0.2903 0.01115 0.00450 -0.1029 0.5610 0.5586
-1.500 0.3191 0.01117 0.00450 -0.1032 0.5592 0.5609
-1.250 0.3480 0.01119 0.00447 -0.1036 0.5576 0.5628
-1.000 0.3769 0.01121 0.00445 -0.1041 0.5560 0.5645
-0.750 0.4058 0.01125 0.00444 -0.1045 0.5545 0.5666
-0.500 0.4349 0.01132 0.00445 -0.1050 0.5531 0.5688
-0.250 0.4640 0.01140 0.00447 -0.1055 0.5517 0.5705
0.000 0.4931 0.01148 0.00453 -0.1060 0.5502 0.5723
0.250 0.5214 0.01149 0.00458 -0.1064 0.5492 0.5743
0.500 0.5498 0.01153 0.00463 -0.1067 0.5480 0.5761
0.750 0.5783 0.01157 0.00469 -0.1071 0.5468 0.5780
1.000 0.6068 0.01163 0.00476 -0.1075 0.5456 0.5801
1.250 0.6353 0.01170 0.00482 -0.1079 0.5443 0.5822
1.500 0.6639 0.01177 0.00488 -0.1083 0.5429 0.5843
1.750 0.6925 0.01183 0.00494 -0.1087 0.5417 0.5864
2.000 0.7209 0.01188 0.00503 -0.1091 0.5406 0.5887
2.250 0.7495 0.01196 0.00513 -0.1095 0.5396 0.5910
2.500 0.7782 0.01206 0.00524 -0.1100 0.5386 0.5936
2.750 0.8070 0.01218 0.00537 -0.1105 0.5377 0.5964
3.000 0.8359 0.01234 0.00552 -0.1110 0.5367 0.5994
3.250 0.8648 0.01255 0.00573 -0.1116 0.5356 0.6024
3.500 0.8925 0.01267 0.00593 -0.1119 0.5346 0.6056
3.750 0.9195 0.01275 0.00609 -0.1120 0.5335 0.6090
4.000 0.9468 0.01286 0.00626 -0.1122 0.5324 0.6127
4.250 0.9743 0.01300 0.00645 -0.1125 0.5314 0.6165
4.500 1.0016 0.01313 0.00665 -0.1127 0.5304 0.6203
4.750 1.0288 0.01326 0.00686 -0.1130 0.5294 0.6245
5.000 1.0562 0.01340 0.00707 -0.1132 0.5283 0.6292
5.250 1.0837 0.01355 0.00726 -0.1135 0.5272 0.6342
5.500 1.1109 0.01368 0.00749 -0.1138 0.5262 0.6392
5.750 1.1385 0.01384 0.00772 -0.1141 0.5253 0.6451
6.000 1.1662 0.01399 0.00793 -0.1144 0.5242 0.6513
6.250 1.1942 0.01412 0.00813 -0.1148 0.5230 0.6580
6.500 1.2229 0.01431 0.00836 -0.1153 0.5217 0.6657
6.750 1.2512 0.01463 0.00875 -0.1158 0.5200 0.6735
7.000 1.2753 0.01473 0.00898 -0.1155 0.5187 0.6826
7.250 1.2989 0.01483 0.00924 -0.1151 0.5168 0.6923
7.500 1.3229 0.01494 0.00949 -0.1147 0.5148 0.7031
7.750 1.3475 0.01504 0.00971 -0.1145 0.5127 0.7156
8.000 1.3740 0.01491 0.00965 -0.1144 0.5093 0.7298
8.250 1.3963 0.01455 0.00935 -0.1134 0.5016 0.7461
8.500 1.4141 0.01399 0.00883 -0.1113 0.4918 0.7654
8.750 1.4261 0.01376 0.00877 -0.1085 0.4829 0.7897
9.000 1.4417 0.01357 0.00867 -0.1062 0.4755 0.8202
9.250 1.4527 0.01353 0.00887 -0.1032 0.4697 0.8661
9.500 1.4751 0.01340 0.00896 -0.1026 0.4620 1.0000
9.750 1.4871 0.01358 0.00920 -0.1001 0.4544 1.0000
10.000 1.4974 0.01383 0.00945 -0.0974 0.4455 1.0000
10.250 1.5056 0.01422 0.00990 -0.0946 0.4320 1.0000
10.500 1.5089 0.01486 0.01054 -0.0913 0.4061 1.0000
10.750 1.4904 0.01663 0.01210 -0.0856 0.3690 1.0000
11.000 1.4666 0.01938 0.01467 -0.0805 0.3328 1.0000
11.250 1.4446 0.02262 0.01778 -0.0767 0.3041 1.0000
11.500 1.4198 0.02652 0.02156 -0.0734 0.2734 1.0000
11.750 1.3967 0.03062 0.02557 -0.0708 0.2488 1.0000
12.000 1.3750 0.03482 0.02968 -0.0686 0.2247 1.0000
12.250 1.3512 0.03942 0.03417 -0.0666 0.1994 1.0000
12.500 1.3311 0.04382 0.03847 -0.0650 0.1737 1.0000
12.750 1.3137 0.04808 0.04261 -0.0637 0.1500 1.0000
13.000 1.2969 0.05236 0.04676 -0.0625 0.1242 1.0000
13.250 1.2821 0.05649 0.05075 -0.0614 0.0987 1.0000
13.500 1.2676 0.06069 0.05476 -0.0605 0.0718 1.0000
13.750 1.2589 0.06432 0.05827 -0.0598 0.0522 1.0000
14.000 1.2501 0.06805 0.06189 -0.0591 0.0364 1.0000
14.250 1.2483 0.07111 0.06491 -0.0587 0.0283 1.0000
14.500 1.2463 0.07427 0.06805 -0.0584 0.0234 1.0000
14.750 1.2498 0.07681 0.07064 -0.0582 0.0211 1.0000
15.000 1.2502 0.07973 0.07358 -0.0580 0.0191 1.0000
15.250 1.2516 0.08260 0.07651 -0.0579 0.0176 1.0000
15.500 1.2555 0.08520 0.07916 -0.0579 0.0167 1.0000
15.750 1.2579 0.08800 0.08202 -0.0579 0.0158 1.0000
16.000 1.2579 0.09109 0.08515 -0.0579 0.0150 1.0000
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Polar data table (+)
Polar graphs
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