FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 50,000 Max Cl/Cd: 44.35 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63100-il-50000-n5.txt Download as CSV file: xf-fx63100-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-100 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3410 0.12201 0.11470 -0.0372 1.0000 0.1030
-9.750 -0.3461 0.11992 0.11271 -0.0387 1.0000 0.1037
-9.500 -0.3509 0.11758 0.11048 -0.0399 1.0000 0.1041
-9.250 -0.3537 0.11488 0.10787 -0.0405 1.0000 0.1042
-8.250 -0.3557 0.09703 0.09028 -0.0421 1.0000 0.0613
-8.000 -0.3599 0.09442 0.08777 -0.0409 1.0000 0.0610
-7.750 -0.3653 0.09201 0.08547 -0.0394 1.0000 0.0607
-7.500 -0.3714 0.08960 0.08317 -0.0379 1.0000 0.0602
-7.250 -0.3782 0.08697 0.08065 -0.0372 1.0000 0.0599
-7.000 -0.3852 0.08413 0.07792 -0.0370 1.0000 0.0595
-6.750 -0.3906 0.08117 0.07504 -0.0373 1.0000 0.0588
-6.500 -0.3947 0.07768 0.07162 -0.0387 1.0000 0.0582
-6.250 -0.3956 0.07347 0.06744 -0.0417 1.0000 0.0575
-6.000 -0.3919 0.06827 0.06222 -0.0466 1.0000 0.0567
-5.750 -0.3815 0.06242 0.05624 -0.0529 0.9998 0.0561
-5.500 -0.3394 0.05372 0.04703 -0.0675 0.9941 0.0574
-5.250 -0.2871 0.04544 0.03776 -0.0816 0.9898 0.0605
-5.000 -0.2395 0.04011 0.03163 -0.0898 0.9866 0.0624
-4.750 -0.2039 0.03795 0.02932 -0.0933 0.9814 0.0675
-4.500 -0.1576 0.03475 0.02535 -0.0987 0.9778 0.0726
-4.250 -0.1186 0.03258 0.02278 -0.1021 0.9730 0.0783
-4.000 -0.0795 0.03096 0.02078 -0.1050 0.9683 0.0849
-3.750 -0.0425 0.02945 0.01888 -0.1069 0.9631 0.0902
-3.500 -0.0076 0.02844 0.01777 -0.1088 0.9574 0.1000
-3.250 0.0261 0.02744 0.01659 -0.1099 0.9517 0.1070
-3.000 0.0602 0.02663 0.01565 -0.1113 0.9453 0.1169
-2.750 0.0990 0.02582 0.01483 -0.1139 0.9403 0.1363
-2.500 0.1359 0.02502 0.01405 -0.1163 0.9334 0.1632
-2.250 0.1824 0.02367 0.01365 -0.1213 0.9293 0.3117
-2.000 0.2134 0.02343 0.01404 -0.1217 0.9219 0.4905
-1.750 0.2456 0.02364 0.01428 -0.1219 0.9145 0.5811
-1.500 0.2705 0.02386 0.01455 -0.1206 0.9056 0.6438
-1.250 0.2980 0.02394 0.01466 -0.1194 0.8983 0.6973
-1.000 0.3205 0.02399 0.01468 -0.1178 0.8885 0.7370
-0.750 0.3534 0.02382 0.01443 -0.1180 0.8821 0.7693
-0.250 0.4127 0.02354 0.01400 -0.1180 0.8656 0.8221
0.000 0.4335 0.02348 0.01392 -0.1165 0.8548 0.8513
0.250 0.4590 0.02329 0.01372 -0.1157 0.8460 0.8896
0.500 0.4934 0.02303 0.01344 -0.1169 0.8371 1.0000
0.750 0.5301 0.02329 0.01356 -0.1192 0.8274 1.0000
1.000 0.5736 0.02335 0.01348 -0.1223 0.8208 1.0000
1.250 0.6058 0.02367 0.01372 -0.1236 0.8100 1.0000
1.500 0.6452 0.02375 0.01372 -0.1257 0.8025 1.0000
1.750 0.6776 0.02401 0.01394 -0.1268 0.7921 1.0000
2.000 0.7090 0.02429 0.01419 -0.1276 0.7816 1.0000
2.250 0.7479 0.02428 0.01416 -0.1292 0.7740 1.0000
2.750 0.8055 0.02492 0.01483 -0.1297 0.7505 1.0000
3.000 0.8399 0.02498 0.01493 -0.1304 0.7409 1.0000
3.250 0.8709 0.02515 0.01514 -0.1307 0.7294 1.0000
3.500 0.8988 0.02542 0.01550 -0.1306 0.7163 1.0000
3.750 0.9277 0.02559 0.01573 -0.1304 0.7027 1.0000
4.000 0.9571 0.02565 0.01586 -0.1301 0.6880 1.0000
4.250 0.9863 0.02566 0.01597 -0.1296 0.6723 1.0000
4.500 1.0149 0.02569 0.01608 -0.1291 0.6560 1.0000
4.750 1.0431 0.02577 0.01625 -0.1285 0.6395 1.0000
5.000 1.0710 0.02587 0.01647 -0.1279 0.6228 1.0000
5.250 1.0985 0.02599 0.01668 -0.1272 0.6054 1.0000
5.500 1.1215 0.02634 0.01717 -0.1261 0.5855 1.0000
5.750 1.1463 0.02658 0.01753 -0.1251 0.5651 1.0000
6.000 1.1699 0.02676 0.01781 -0.1237 0.5409 1.0000
6.250 1.1911 0.02696 0.01803 -0.1219 0.5108 1.0000
6.500 1.2103 0.02729 0.01833 -0.1198 0.4766 1.0000
6.750 1.2289 0.02778 0.01876 -0.1179 0.4425 1.0000
7.000 1.2464 0.02847 0.01944 -0.1159 0.4094 1.0000
7.250 1.2608 0.02937 0.02032 -0.1138 0.3735 1.0000
7.500 1.2716 0.03046 0.02129 -0.1113 0.3329 1.0000
7.750 1.2791 0.03181 0.02245 -0.1086 0.2896 1.0000
8.000 1.2840 0.03341 0.02382 -0.1058 0.2495 1.0000
8.250 1.2868 0.03521 0.02540 -0.1029 0.2165 1.0000
8.500 1.2911 0.03713 0.02721 -0.1004 0.1894 1.0000
8.750 1.2953 0.03916 0.02919 -0.0982 0.1678 1.0000
9.000 1.3009 0.04122 0.03124 -0.0961 0.1500 1.0000
9.250 1.3072 0.04335 0.03337 -0.0943 0.1368 1.0000
9.500 1.3141 0.04552 0.03552 -0.0926 0.1267 1.0000
9.750 1.3243 0.04759 0.03769 -0.0911 0.1174 1.0000
10.000 1.3362 0.04965 0.03985 -0.0897 0.1095 1.0000
10.250 1.3465 0.05175 0.04196 -0.0885 0.1026 1.0000
10.500 1.3611 0.05382 0.04425 -0.0873 0.0961 1.0000
10.750 1.3780 0.05585 0.04643 -0.0863 0.0913 1.0000
11.000 1.4005 0.05799 0.04866 -0.0855 0.0872 1.0000
11.250 1.4130 0.06064 0.05170 -0.0844 0.0830 1.0000
11.500 1.4215 0.06324 0.05447 -0.0834 0.0789 1.0000
11.750 1.4387 0.06588 0.05710 -0.0827 0.0753 1.0000
12.000 1.4373 0.06959 0.06131 -0.0815 0.0731 1.0000
12.250 1.4322 0.07353 0.06566 -0.0805 0.0708 1.0000
12.500 1.4254 0.07758 0.07001 -0.0799 0.0684 1.0000
12.750 1.4202 0.08153 0.07418 -0.0796 0.0662 1.0000
13.000 1.4217 0.08506 0.07783 -0.0794 0.0639 1.0000
13.250 1.4111 0.09013 0.08314 -0.0798 0.0627 1.0000
13.500 1.3891 0.09653 0.08991 -0.0814 0.0622 1.0000
13.750 1.3659 0.10360 0.09731 -0.0840 0.0619 1.0000
14.000 1.3404 0.11158 0.10552 -0.0878 0.0618 1.0000
14.250 1.3136 0.12058 0.11477 -0.0930 0.0620 1.0000
14.500 1.2862 0.13073 0.12511 -0.0994 0.0624 1.0000
14.750 1.2581 0.14240 0.13692 -0.1073 0.0628 1.0000
15.000 1.2309 0.15544 0.15002 -0.1162 0.0632 1.0000
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Polar data table (+)
Polar graphs
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