RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il) Reynolds number: 500,000 Max Cl/Cd: 105.1 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r1082-il-500000.txt Download as CSV file: xf-r1082-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1082 VOYAGER ROOT OUTER AFT WING 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2345 0.07467 0.07173 -0.1049 0.8071 0.0218
-13.000 -0.5814 0.05106 0.04762 -0.1068 0.9376 0.0173
-12.750 -0.5542 0.04395 0.04015 -0.1189 0.9160 0.0170
-12.500 -0.5458 0.03851 0.03409 -0.1260 0.8650 0.0169
-12.250 -0.5559 0.03616 0.03131 -0.1237 0.8261 0.0169
-12.000 -0.5620 0.03410 0.02896 -0.1210 0.8022 0.0168
-11.750 -0.5651 0.03245 0.02706 -0.1182 0.7839 0.0168
-11.500 -0.5671 0.03087 0.02520 -0.1152 0.7694 0.0168
-11.250 -0.5640 0.02921 0.02329 -0.1126 0.7575 0.0167
-11.000 -0.5607 0.02798 0.02182 -0.1098 0.7467 0.0169
-10.750 -0.5543 0.02686 0.02047 -0.1072 0.7376 0.0170
-10.500 -0.5408 0.02552 0.01895 -0.1056 0.7292 0.0170
-10.250 -0.5293 0.02456 0.01779 -0.1035 0.7220 0.0171
-10.000 -0.5146 0.02369 0.01676 -0.1019 0.7150 0.0172
-9.750 -0.4909 0.02221 0.01512 -0.1018 0.7091 0.0174
-9.500 -0.4683 0.02099 0.01387 -0.1015 0.7036 0.0179
-9.250 -0.4504 0.02036 0.01319 -0.1003 0.6980 0.0183
-9.000 -0.4318 0.01968 0.01242 -0.0992 0.6929 0.0187
-8.750 -0.4135 0.01911 0.01177 -0.0979 0.6882 0.0192
-8.500 -0.3950 0.01845 0.01107 -0.0967 0.6836 0.0196
-8.250 -0.3773 0.01786 0.01039 -0.0952 0.6792 0.0199
-8.000 -0.3599 0.01737 0.00981 -0.0937 0.6754 0.0204
-7.750 -0.3432 0.01691 0.00928 -0.0920 0.6719 0.0206
-7.500 -0.3305 0.01626 0.00861 -0.0896 0.6684 0.0212
-7.250 -0.3159 0.01577 0.00811 -0.0875 0.6651 0.0220
-7.000 -0.2979 0.01539 0.00769 -0.0860 0.6620 0.0227
-6.750 -0.2790 0.01504 0.00727 -0.0846 0.6591 0.0238
-6.500 -0.2596 0.01470 0.00686 -0.0833 0.6562 0.0250
-6.250 -0.2410 0.01428 0.00646 -0.0819 0.6538 0.0267
-6.000 -0.2200 0.01398 0.00614 -0.0808 0.6511 0.0295
-5.750 -0.2002 0.01360 0.00578 -0.0795 0.6485 0.0347
-5.500 -0.1827 0.01308 0.00538 -0.0779 0.6460 0.0543
-5.250 -0.1632 0.01269 0.00511 -0.0767 0.6436 0.0808
-5.000 -0.1413 0.01245 0.00491 -0.0758 0.6412 0.1033
-4.750 -0.1194 0.01220 0.00475 -0.0750 0.6391 0.1288
-4.500 -0.0984 0.01188 0.00457 -0.0740 0.6372 0.1612
-4.250 -0.0783 0.01150 0.00439 -0.0729 0.6353 0.2063
-4.000 -0.0599 0.01103 0.00420 -0.0716 0.6333 0.2742
-3.750 -0.0443 0.01040 0.00397 -0.0698 0.6314 0.3726
-3.500 -0.0316 0.00961 0.00371 -0.0675 0.6296 0.5053
-3.250 -0.0171 0.00901 0.00369 -0.0650 0.6279 0.6424
-3.000 0.0080 0.00913 0.00395 -0.0642 0.6262 0.7075
-2.750 0.0358 0.00932 0.00406 -0.0642 0.6245 0.7296
-2.500 0.0640 0.00955 0.00424 -0.0642 0.6227 0.7434
-2.250 0.0913 0.00969 0.00437 -0.0640 0.6211 0.7540
-2.000 0.1187 0.00985 0.00449 -0.0638 0.6194 0.7640
-1.750 0.1466 0.01000 0.00465 -0.0637 0.6179 0.7708
-1.500 0.1744 0.01017 0.00479 -0.0637 0.6163 0.7779
-1.250 0.2022 0.01029 0.00486 -0.0637 0.6148 0.7845
-1.000 0.2303 0.01048 0.00506 -0.0635 0.6133 0.7899
-0.750 0.2579 0.01069 0.00523 -0.0634 0.6119 0.7979
-0.500 0.2853 0.01090 0.00544 -0.0631 0.6105 0.8044
-0.250 0.3130 0.01114 0.00567 -0.0629 0.6090 0.8107
0.000 0.3414 0.01134 0.00579 -0.0632 0.6074 0.8166
0.250 0.3688 0.01145 0.00591 -0.0631 0.6059 0.8197
0.500 0.3956 0.01152 0.00601 -0.0629 0.6048 0.8224
0.750 0.4226 0.01160 0.00609 -0.0629 0.6035 0.8253
1.000 0.4499 0.01165 0.00615 -0.0630 0.6020 0.8283
1.250 0.4775 0.01169 0.00618 -0.0632 0.6003 0.8312
1.500 0.5058 0.01174 0.00621 -0.0637 0.5987 0.8338
1.750 0.5330 0.01174 0.00621 -0.0637 0.5972 0.8356
2.000 0.5607 0.01178 0.00625 -0.0639 0.5956 0.8373
2.250 0.5888 0.01183 0.00629 -0.0641 0.5940 0.8392
2.500 0.6174 0.01190 0.00635 -0.0645 0.5925 0.8409
2.750 0.6465 0.01203 0.00645 -0.0651 0.5907 0.8428
3.000 0.6739 0.01213 0.00657 -0.0653 0.5890 0.8447
3.250 0.7001 0.01214 0.00662 -0.0653 0.5871 0.8466
3.500 0.7269 0.01217 0.00668 -0.0655 0.5850 0.8485
3.750 0.7544 0.01220 0.00673 -0.0658 0.5828 0.8500
4.000 0.7820 0.01219 0.00674 -0.0660 0.5805 0.8513
4.250 0.8096 0.01218 0.00673 -0.0662 0.5783 0.8527
4.500 0.8383 0.01220 0.00675 -0.0666 0.5760 0.8541
4.750 0.8680 0.01237 0.00690 -0.0673 0.5734 0.8554
5.000 0.8915 0.01233 0.00695 -0.0667 0.5709 0.8569
5.250 0.9163 0.01232 0.00700 -0.0664 0.5678 0.8584
5.500 0.9428 0.01229 0.00701 -0.0664 0.5646 0.8600
5.750 0.9707 0.01225 0.00696 -0.0667 0.5613 0.8618
6.000 1.0003 0.01228 0.00696 -0.0673 0.5579 0.8635
6.250 1.0235 0.01227 0.00703 -0.0667 0.5542 0.8652
6.500 1.0476 0.01222 0.00704 -0.0663 0.5498 0.8668
6.750 1.0732 0.01212 0.00697 -0.0661 0.5456 0.8682
7.000 1.1009 0.01210 0.00693 -0.0663 0.5414 0.8696
7.250 1.1203 0.01206 0.00701 -0.0649 0.5369 0.8715
7.500 1.1421 0.01200 0.00702 -0.0639 0.5315 0.8734
7.750 1.1662 0.01195 0.00698 -0.0634 0.5265 0.8755
8.000 1.1854 0.01195 0.00708 -0.0620 0.5207 0.8781
8.250 1.2046 0.01190 0.00710 -0.0605 0.5139 0.8806
8.500 1.2241 0.01191 0.00714 -0.0592 0.5067 0.8828
8.750 1.2385 0.01188 0.00718 -0.0568 0.4976 0.8854
9.000 1.2496 0.01189 0.00726 -0.0538 0.4874 0.8884
9.250 1.2600 0.01199 0.00740 -0.0507 0.4755 0.8919
9.500 1.2679 0.01220 0.00763 -0.0472 0.4585 0.8959
9.750 1.2714 0.01257 0.00795 -0.0432 0.4376 0.9004
10.000 1.2669 0.01316 0.00848 -0.0379 0.4143 0.9066
10.250 1.2574 0.01410 0.00932 -0.0323 0.3897 0.9141
10.500 1.2479 0.01514 0.01034 -0.0271 0.3670 0.9230
10.750 1.2379 0.01644 0.01160 -0.0223 0.3454 0.9358
11.000 1.2355 0.01811 0.01325 -0.0198 0.3214 0.9569
11.250 1.2393 0.02035 0.01541 -0.0199 0.2947 1.0000
11.500 1.2349 0.02241 0.01739 -0.0178 0.2733 1.0000
11.750 1.2290 0.02463 0.01953 -0.0156 0.2533 1.0000
12.000 1.2232 0.02691 0.02173 -0.0136 0.2352 1.0000
12.250 1.2159 0.02936 0.02408 -0.0116 0.2147 1.0000
12.500 1.2143 0.03145 0.02612 -0.0101 0.2003 1.0000
12.750 1.2108 0.03375 0.02835 -0.0086 0.1827 1.0000
13.000 1.2082 0.03603 0.03056 -0.0073 0.1667 1.0000
13.250 1.2068 0.03829 0.03275 -0.0061 0.1517 1.0000
13.500 1.2071 0.04046 0.03486 -0.0051 0.1382 1.0000
13.750 1.2083 0.04261 0.03695 -0.0042 0.1264 1.0000
14.000 1.2099 0.04476 0.03907 -0.0035 0.1158 1.0000
14.250 1.2126 0.04686 0.04113 -0.0028 0.1059 1.0000
14.500 1.2173 0.04883 0.04310 -0.0023 0.0977 1.0000
14.750 1.2207 0.05095 0.04520 -0.0018 0.0899 1.0000
15.000 1.2242 0.05308 0.04731 -0.0014 0.0828 1.0000
15.250 1.2293 0.05512 0.04937 -0.0011 0.0767 1.0000
15.500 1.2323 0.05738 0.05162 -0.0008 0.0710 1.0000
15.750 1.2377 0.05948 0.05374 -0.0006 0.0658 1.0000
16.000 1.2403 0.06185 0.05611 -0.0005 0.0613 1.0000
16.250 1.2462 0.06394 0.05824 -0.0004 0.0574 1.0000
16.500 1.2490 0.06639 0.06071 -0.0004 0.0535 1.0000
16.750 1.2536 0.06870 0.06305 -0.0005 0.0498 1.0000
17.000 1.2569 0.07118 0.06557 -0.0006 0.0466 1.0000
17.250 1.2586 0.07387 0.06828 -0.0008 0.0435 1.0000
17.500 1.2630 0.07630 0.07077 -0.0011 0.0404 1.0000
17.750 1.2624 0.07937 0.07385 -0.0014 0.0375 1.0000
18.000 1.2662 0.08196 0.07651 -0.0018 0.0344 1.0000
18.250 1.2652 0.08518 0.07974 -0.0024 0.0320 1.0000
18.500 1.2664 0.08818 0.08281 -0.0030 0.0288 1.0000
19.000 1.2633 0.09503 0.08976 -0.0046 0.0242 1.0000
19.250 1.2598 0.09882 0.09359 -0.0056 0.0227 1.0000
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Polar data table (+)
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