RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il) Reynolds number: 500,000 Max Cl/Cd: 102.18 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r1080-il-500000-n5.txt Download as CSV file: xf-r1080-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RONCZ 1080 VOYAGER INNER 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.5409 0.08963 0.08558 -0.0927 0.7597 0.0086
-16.250 -0.5726 0.07915 0.07485 -0.0990 0.7551 0.0085
-16.000 -0.5973 0.07072 0.06622 -0.1042 0.7491 0.0085
-15.750 -0.6194 0.06344 0.05874 -0.1087 0.7425 0.0085
-15.500 -0.6321 0.05819 0.05329 -0.1116 0.7359 0.0084
-15.250 -0.6430 0.05370 0.04865 -0.1138 0.7294 0.0084
-15.000 -0.6576 0.04923 0.04398 -0.1154 0.7232 0.0085
-14.750 -0.6677 0.04567 0.04024 -0.1161 0.7177 0.0085
-14.500 -0.6732 0.04286 0.03727 -0.1162 0.7122 0.0085
-14.250 -0.6792 0.04019 0.03444 -0.1157 0.7070 0.0086
-14.000 -0.6814 0.03804 0.03216 -0.1151 0.7021 0.0086
-13.750 -0.6814 0.03614 0.03014 -0.1142 0.6978 0.0087
-13.500 -0.6803 0.03438 0.02826 -0.1131 0.6932 0.0088
-13.250 -0.6756 0.03301 0.02679 -0.1119 0.6891 0.0089
-13.000 -0.6733 0.03139 0.02502 -0.1104 0.6854 0.0089
-12.750 -0.6663 0.03021 0.02375 -0.1092 0.6821 0.0090
-12.500 -0.6596 0.02896 0.02240 -0.1077 0.6786 0.0091
-12.250 -0.6505 0.02795 0.02128 -0.1063 0.6752 0.0092
-12.000 -0.6414 0.02692 0.02015 -0.1048 0.6719 0.0093
-11.500 -0.6201 0.02506 0.01809 -0.1018 0.6663 0.0096
-11.250 -0.6083 0.02417 0.01711 -0.1003 0.6635 0.0097
-11.000 -0.5958 0.02333 0.01618 -0.0988 0.6609 0.0098
-10.750 -0.5822 0.02258 0.01535 -0.0974 0.6583 0.0100
-10.500 -0.5674 0.02195 0.01462 -0.0960 0.6560 0.0102
-10.250 -0.5529 0.02125 0.01383 -0.0945 0.6538 0.0104
-10.000 -0.5375 0.02065 0.01313 -0.0931 0.6517 0.0106
-9.750 -0.5215 0.02007 0.01248 -0.0917 0.6500 0.0107
-9.500 -0.5068 0.01940 0.01176 -0.0902 0.6483 0.0110
-9.250 -0.4920 0.01875 0.01108 -0.0886 0.6464 0.0112
-9.000 -0.4760 0.01820 0.01050 -0.0870 0.6446 0.0116
-8.750 -0.4594 0.01770 0.00996 -0.0855 0.6428 0.0118
-8.500 -0.4426 0.01724 0.00945 -0.0840 0.6411 0.0121
-8.250 -0.4258 0.01681 0.00897 -0.0824 0.6395 0.0124
-8.000 -0.4092 0.01644 0.00854 -0.0807 0.6379 0.0128
-7.750 -0.3923 0.01610 0.00814 -0.0790 0.6364 0.0130
-7.500 -0.3744 0.01579 0.00777 -0.0775 0.6349 0.0134
-7.250 -0.3559 0.01540 0.00735 -0.0760 0.6335 0.0140
-7.000 -0.3356 0.01507 0.00701 -0.0750 0.6321 0.0146
-6.750 -0.3146 0.01477 0.00668 -0.0739 0.6306 0.0153
-6.500 -0.2930 0.01449 0.00637 -0.0730 0.6293 0.0162
-6.250 -0.2717 0.01419 0.00606 -0.0721 0.6280 0.0175
-6.000 -0.2496 0.01393 0.00579 -0.0712 0.6267 0.0191
-5.750 -0.2278 0.01365 0.00551 -0.0703 0.6254 0.0221
-5.500 -0.2056 0.01339 0.00525 -0.0695 0.6242 0.0265
-5.250 -0.1833 0.01313 0.00501 -0.0687 0.6230 0.0333
-5.000 -0.1609 0.01288 0.00479 -0.0679 0.6219 0.0434
-4.750 -0.1384 0.01263 0.00459 -0.0672 0.6208 0.0570
-4.500 -0.1156 0.01239 0.00441 -0.0665 0.6197 0.0724
-4.250 -0.0926 0.01216 0.00424 -0.0658 0.6186 0.0925
-3.750 -0.0471 0.01165 0.00393 -0.0645 0.6166 0.1468
-3.500 -0.0270 0.01122 0.00376 -0.0634 0.6157 0.2046
-3.250 -0.0081 0.01071 0.00357 -0.0622 0.6146 0.2825
-3.000 0.0107 0.01020 0.00338 -0.0609 0.6133 0.3655
-2.750 0.0288 0.00965 0.00318 -0.0595 0.6122 0.4601
-2.500 0.0459 0.00904 0.00301 -0.0577 0.6112 0.5702
-2.250 0.0671 0.00878 0.00310 -0.0565 0.6102 0.6601
-2.000 0.0940 0.00882 0.00318 -0.0563 0.6092 0.6951
-1.750 0.1219 0.00888 0.00323 -0.0563 0.6082 0.7129
-1.500 0.1500 0.00895 0.00327 -0.0564 0.6072 0.7254
-1.250 0.1782 0.00903 0.00333 -0.0565 0.6063 0.7346
-1.000 0.2065 0.00911 0.00335 -0.0567 0.6053 0.7447
-0.750 0.2345 0.00923 0.00349 -0.0567 0.6044 0.7545
-0.500 0.2625 0.00935 0.00357 -0.0568 0.6033 0.7637
-0.250 0.2908 0.00948 0.00370 -0.0568 0.6022 0.7704
0.000 0.3193 0.00960 0.00377 -0.0571 0.6012 0.7758
0.250 0.3479 0.00966 0.00380 -0.0575 0.6004 0.7790
0.500 0.3762 0.00969 0.00383 -0.0577 0.5996 0.7809
0.750 0.4045 0.00972 0.00388 -0.0580 0.5986 0.7827
1.000 0.4327 0.00976 0.00393 -0.0582 0.5974 0.7845
1.250 0.4610 0.00981 0.00398 -0.0585 0.5962 0.7862
1.500 0.4893 0.00985 0.00403 -0.0588 0.5950 0.7880
1.750 0.5176 0.00989 0.00407 -0.0591 0.5937 0.7897
2.000 0.5458 0.00993 0.00411 -0.0594 0.5922 0.7914
2.250 0.5742 0.00996 0.00413 -0.0597 0.5907 0.7928
2.500 0.6025 0.00999 0.00415 -0.0601 0.5891 0.7943
2.750 0.6309 0.01003 0.00417 -0.0604 0.5874 0.7958
3.000 0.6596 0.01008 0.00420 -0.0608 0.5857 0.7970
3.250 0.6878 0.01013 0.00426 -0.0611 0.5839 0.7981
3.500 0.7144 0.01015 0.00434 -0.0611 0.5818 0.7992
3.750 0.7412 0.01016 0.00440 -0.0611 0.5790 0.8004
4.000 0.7682 0.01018 0.00445 -0.0612 0.5761 0.8018
4.250 0.7953 0.01018 0.00448 -0.0612 0.5733 0.8033
4.500 0.8227 0.01019 0.00449 -0.0614 0.5703 0.8046
4.750 0.8493 0.01022 0.00454 -0.0614 0.5669 0.8060
5.000 0.8748 0.01023 0.00462 -0.0612 0.5627 0.8074
5.250 0.9006 0.01024 0.00466 -0.0610 0.5583 0.8088
5.500 0.9268 0.01025 0.00467 -0.0609 0.5542 0.8102
5.750 0.9524 0.01029 0.00476 -0.0607 0.5498 0.8116
6.000 0.9773 0.01032 0.00486 -0.0604 0.5439 0.8131
6.250 1.0018 0.01035 0.00489 -0.0600 0.5382 0.8146
6.500 1.0255 0.01039 0.00501 -0.0595 0.5306 0.8162
6.750 1.0477 0.01043 0.00507 -0.0586 0.5215 0.8178
7.000 1.0689 0.01050 0.00518 -0.0576 0.5090 0.8194
7.250 1.0862 0.01063 0.00528 -0.0558 0.4903 0.8213
7.500 1.0942 0.01091 0.00546 -0.0523 0.4633 0.8236
7.750 1.0915 0.01140 0.00582 -0.0468 0.4344 0.8264
8.000 1.0889 0.01209 0.00639 -0.0416 0.4079 0.8293
8.250 1.0851 0.01289 0.00709 -0.0366 0.3843 0.8322
8.500 1.0810 0.01378 0.00793 -0.0319 0.3613 0.8354
8.750 1.0736 0.01494 0.00903 -0.0271 0.3384 0.8394
9.000 1.0689 0.01621 0.01024 -0.0232 0.3185 0.8436
9.250 1.0659 0.01759 0.01156 -0.0198 0.2995 0.8474
9.500 1.0633 0.01904 0.01299 -0.0167 0.2817 0.8513
9.750 1.0596 0.02064 0.01455 -0.0138 0.2626 0.8558
10.000 1.0601 0.02211 0.01599 -0.0114 0.2474 0.8607
10.500 1.0606 0.02518 0.01901 -0.0069 0.2160 0.8715
10.750 1.0641 0.02656 0.02038 -0.0051 0.2034 0.8782
11.000 1.0668 0.02801 0.02182 -0.0032 0.1899 0.8860
11.250 1.0711 0.02939 0.02321 -0.0016 0.1787 0.8965
11.500 1.0763 0.03081 0.02465 -0.0002 0.1668 0.9120
11.750 1.0909 0.03233 0.02622 -0.0010 0.1540 0.9342
12.000 1.1160 0.03406 0.02795 -0.0042 0.1406 0.9636
12.500 1.1300 0.03697 0.03081 -0.0023 0.1227 1.0000
12.750 1.1388 0.03838 0.03221 -0.0016 0.1147 1.0000
13.000 1.1468 0.03990 0.03371 -0.0009 0.1073 1.0000
13.250 1.1549 0.04142 0.03522 -0.0003 0.1005 1.0000
13.500 1.1639 0.04288 0.03668 0.0003 0.0941 1.0000
13.750 1.1711 0.04453 0.03832 0.0009 0.0882 1.0000
14.000 1.1805 0.04602 0.03982 0.0013 0.0827 1.0000
14.250 1.1875 0.04772 0.04152 0.0018 0.0772 1.0000
14.500 1.1952 0.04941 0.04321 0.0022 0.0711 1.0000
14.750 1.2016 0.05122 0.04501 0.0027 0.0658 1.0000
15.000 1.2100 0.05289 0.04670 0.0029 0.0616 1.0000
15.250 1.2156 0.05485 0.04865 0.0033 0.0573 1.0000
15.500 1.2244 0.05653 0.05037 0.0035 0.0541 1.0000
15.750 1.2315 0.05841 0.05228 0.0036 0.0513 1.0000
16.000 1.2377 0.06041 0.05430 0.0038 0.0488 1.0000
16.250 1.2459 0.06222 0.05617 0.0038 0.0467 1.0000
16.500 1.2518 0.06430 0.05830 0.0039 0.0444 1.0000
16.750 1.2568 0.06651 0.06053 0.0039 0.0422 1.0000
17.000 1.2639 0.06854 0.06262 0.0038 0.0403 1.0000
17.250 1.2692 0.07080 0.06494 0.0036 0.0386 1.0000
17.500 1.2732 0.07320 0.06737 0.0034 0.0365 1.0000
17.750 1.2776 0.07561 0.06985 0.0031 0.0347 1.0000
18.000 1.2824 0.07801 0.07231 0.0028 0.0330 1.0000
18.250 1.2848 0.08075 0.07510 0.0024 0.0314 1.0000
18.500 1.2880 0.08342 0.07783 0.0019 0.0298 1.0000
18.750 1.2910 0.08616 0.08064 0.0013 0.0285 1.0000
19.000 1.2928 0.08907 0.08361 0.0007 0.0270 1.0000
19.250 1.2930 0.09224 0.08684 -0.0001 0.0256 1.0000
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